Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Xfoil prediction polar at RE=2,000,000 Ncrit=9
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Airfoil: Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Reynolds number: 2,000,000 Max Cl/Cd: 119.38 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-root-ns-2000000.txt Download as CSV file: xf-prandtl-d-root-ns-2000000.csv |
XFOIL Version 6.96
Calculated polar for: Prandtl-D root - NASA Preliminary Research Aerod
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 2.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.6829 0.23474 0.23366 0.0652 1.0000 0.0039
-18.000 -0.6741 0.23143 0.23034 0.0630 1.0000 0.0039
-17.750 -0.6642 0.22919 0.22810 0.0611 1.0000 0.0040
-17.500 -0.6551 0.22596 0.22487 0.0589 1.0000 0.0041
-17.250 -0.6455 0.22321 0.22213 0.0569 1.0000 0.0043
-17.000 -0.6365 0.21991 0.21883 0.0547 1.0000 0.0044
-16.750 -0.6272 0.21678 0.21570 0.0526 1.0000 0.0048
-16.500 -0.6183 0.21258 0.21151 0.0503 1.0000 0.0055
-16.250 -0.6110 0.20883 0.20762 0.0483 0.9339 0.0056
-16.000 -0.6042 0.20522 0.20397 0.0466 0.9216 0.0056
-15.750 -0.5968 0.20157 0.20028 0.0447 0.9137 0.0056
-15.500 -0.5892 0.19792 0.19660 0.0428 0.9067 0.0056
-15.250 -0.4912 0.18368 0.18235 0.0509 0.8095 0.0057
-15.000 -0.4882 0.17922 0.17788 0.0484 0.8060 0.0058
-14.750 -0.4801 0.17676 0.17539 0.0466 0.8003 0.0059
-14.500 -0.4732 0.17376 0.17237 0.0446 0.7955 0.0059
-14.250 -0.4656 0.17119 0.16978 0.0426 0.7899 0.0060
-14.000 -0.4578 0.16863 0.16718 0.0407 0.7836 0.0063
-13.750 -0.4514 0.16565 0.16419 0.0386 0.7790 0.0063
-13.500 -0.4446 0.16283 0.16134 0.0365 0.7734 0.0066
-13.250 -0.4384 0.15980 0.15828 0.0344 0.7681 0.0069
-13.000 -0.7433 0.09855 0.09700 -0.0057 0.8787 0.0061
-12.750 -0.8242 0.07970 0.07801 -0.0172 0.8753 0.0059
-12.500 -0.8327 0.07456 0.07285 -0.0201 0.8697 0.0058
-12.250 -0.9871 0.04159 0.03957 -0.0451 0.8570 0.0055
-12.000 -1.0086 0.03777 0.03557 -0.0440 0.8469 0.0055
-11.750 -1.0246 0.03512 0.03276 -0.0408 0.8376 0.0055
-11.500 -1.0341 0.03195 0.02934 -0.0384 0.8285 0.0055
-11.250 -1.0243 0.03035 0.02760 -0.0371 0.8206 0.0056
-11.000 -1.0179 0.02827 0.02531 -0.0354 0.8121 0.0056
-10.750 -0.9957 0.02784 0.02483 -0.0348 0.8033 0.0056
-10.500 -0.9822 0.02634 0.02316 -0.0336 0.7946 0.0057
-10.250 -0.9925 0.02165 0.01790 -0.0299 0.7851 0.0059
-10.000 -0.9763 0.02020 0.01627 -0.0286 0.7768 0.0061
-9.750 -0.9555 0.01934 0.01528 -0.0277 0.7679 0.0063
-9.500 -0.9344 0.01845 0.01426 -0.0268 0.7594 0.0063
-9.250 -0.9114 0.01779 0.01351 -0.0262 0.7507 0.0064
-9.000 -0.8871 0.01731 0.01295 -0.0257 0.7419 0.0066
-8.750 -0.8638 0.01666 0.01220 -0.0250 0.7339 0.0067
-8.500 -0.8393 0.01616 0.01161 -0.0245 0.7256 0.0068
-8.250 -0.8154 0.01554 0.01089 -0.0239 0.7181 0.0069
-8.000 -0.7908 0.01502 0.01027 -0.0234 0.7104 0.0071
-7.750 -0.7660 0.01449 0.00965 -0.0229 0.7036 0.0072
-7.500 -0.7412 0.01396 0.00902 -0.0224 0.6963 0.0073
-7.250 -0.7159 0.01348 0.00845 -0.0219 0.6898 0.0075
-7.000 -0.6903 0.01303 0.00792 -0.0215 0.6835 0.0076
-6.750 -0.6644 0.01264 0.00744 -0.0211 0.6771 0.0077
-6.500 -0.6381 0.01228 0.00703 -0.0208 0.6718 0.0079
-6.250 -0.6114 0.01199 0.00667 -0.0205 0.6658 0.0080
-6.000 -0.5878 0.01113 0.00566 -0.0197 0.6602 0.0085
-5.750 -0.5612 0.01077 0.00526 -0.0194 0.6552 0.0090
-5.500 -0.5341 0.01053 0.00498 -0.0192 0.6499 0.0093
-5.250 -0.5068 0.01030 0.00472 -0.0190 0.6449 0.0098
-5.000 -0.4793 0.01009 0.00448 -0.0189 0.6403 0.0102
-4.750 -0.4516 0.00993 0.00428 -0.0188 0.6351 0.0106
-4.500 -0.4239 0.00977 0.00408 -0.0187 0.6303 0.0108
-4.250 -0.3977 0.00927 0.00352 -0.0182 0.6263 0.0120
-4.000 -0.3701 0.00908 0.00330 -0.0181 0.6217 0.0127
-3.750 -0.3423 0.00892 0.00310 -0.0180 0.6166 0.0135
-3.500 -0.3143 0.00876 0.00293 -0.0180 0.6129 0.0140
-3.250 -0.2866 0.00855 0.00267 -0.0178 0.6087 0.0148
-3.000 -0.2591 0.00833 0.00242 -0.0177 0.6042 0.0164
-2.750 -0.2311 0.00818 0.00224 -0.0176 0.6000 0.0176
-2.500 -0.2029 0.00806 0.00211 -0.0176 0.5966 0.0185
-2.250 -0.1752 0.00785 0.00189 -0.0175 0.5925 0.0220
-2.000 -0.1474 0.00768 0.00172 -0.0174 0.5881 0.0289
-1.750 -0.1198 0.00749 0.00162 -0.0173 0.5844 0.0476
-1.500 -0.0916 0.00737 0.00152 -0.0173 0.5811 0.0544
-1.250 -0.0632 0.00730 0.00144 -0.0174 0.5773 0.0571
-1.000 -0.0347 0.00725 0.00136 -0.0174 0.5730 0.0596
-0.750 -0.0065 0.00715 0.00128 -0.0174 0.5693 0.0666
-0.500 0.0214 0.00700 0.00121 -0.0174 0.5659 0.0852
-0.250 0.0494 0.00687 0.00114 -0.0174 0.5622 0.1071
0.000 0.0772 0.00674 0.00108 -0.0174 0.5582 0.1338
0.250 0.1050 0.00660 0.00104 -0.0174 0.5545 0.1662
0.500 0.1325 0.00642 0.00100 -0.0174 0.5511 0.2107
0.750 0.1602 0.00630 0.00097 -0.0174 0.5472 0.2467
1.000 0.1879 0.00620 0.00095 -0.0174 0.5430 0.2843
1.250 0.2155 0.00607 0.00094 -0.0173 0.5394 0.3270
1.500 0.2430 0.00593 0.00093 -0.0173 0.5359 0.3733
1.750 0.2701 0.00579 0.00093 -0.0172 0.5319 0.4275
2.000 0.2968 0.00566 0.00094 -0.0170 0.5273 0.4864
2.250 0.3228 0.00546 0.00095 -0.0167 0.5239 0.5642
2.500 0.3470 0.00519 0.00096 -0.0160 0.5195 0.6618
2.750 0.3638 0.00443 0.00105 -0.0134 0.5148 0.9444
3.000 0.3985 0.00454 0.00114 -0.0148 0.5099 0.9611
3.250 0.4259 0.00461 0.00121 -0.0146 0.5058 0.9694
3.500 0.4690 0.00478 0.00133 -0.0180 0.4984 0.9738
3.750 0.5064 0.00489 0.00141 -0.0201 0.4885 0.9761
4.000 0.5407 0.00503 0.00150 -0.0215 0.4802 0.9786
4.250 0.5675 0.00517 0.00163 -0.0212 0.4724 0.9829
4.500 0.6136 0.00537 0.00173 -0.0253 0.4542 0.9841
4.750 0.6574 0.00558 0.00185 -0.0290 0.4324 0.9855
5.000 0.6960 0.00583 0.00198 -0.0316 0.4040 0.9869
5.250 0.7342 0.00623 0.00217 -0.0342 0.3624 0.9886
5.500 0.7701 0.00700 0.00255 -0.0367 0.2821 0.9910
5.750 0.7993 0.00833 0.00328 -0.0382 0.1611 0.9939
6.000 0.8370 0.00937 0.00386 -0.0415 0.0704 0.9952
6.250 0.8674 0.00998 0.00427 -0.0427 0.0290 0.9960
6.500 0.8937 0.01044 0.00463 -0.0429 0.0083 0.9964
6.750 0.9206 0.01065 0.00484 -0.0430 0.0076 0.9967
7.000 0.9473 0.01088 0.00507 -0.0431 0.0072 0.9970
7.250 0.9739 0.01112 0.00533 -0.0432 0.0070 0.9973
7.500 1.0002 0.01138 0.00560 -0.0433 0.0069 0.9977
7.750 1.0264 0.01167 0.00590 -0.0434 0.0066 0.9981
8.000 1.0523 0.01199 0.00623 -0.0434 0.0064 0.9985
8.250 1.0778 0.01237 0.00662 -0.0435 0.0060 0.9989
8.500 1.1033 0.01275 0.00702 -0.0435 0.0059 0.9993
8.750 1.1284 0.01322 0.00752 -0.0436 0.0056 0.9997
9.000 1.1511 0.01373 0.00806 -0.0433 0.0055 1.0000
9.250 1.1672 0.01432 0.00869 -0.0417 0.0053 1.0000
9.500 1.1817 0.01492 0.00934 -0.0398 0.0052 1.0000
9.750 1.1910 0.01571 0.01018 -0.0372 0.0051 1.0000
10.000 1.1937 0.01664 0.01118 -0.0335 0.0051 1.0000
10.250 1.1844 0.01733 0.01192 -0.0277 0.0051 1.0000
10.500 1.1772 0.01816 0.01281 -0.0227 0.0051 1.0000
10.750 1.1761 0.01914 0.01383 -0.0190 0.0051 1.0000
11.000 1.1777 0.02023 0.01496 -0.0161 0.0050 1.0000
11.250 1.1942 0.02060 0.01535 -0.0149 0.0049 1.0000
11.500 1.1948 0.02203 0.01683 -0.0124 0.0049 1.0000
11.750 1.1978 0.02345 0.01831 -0.0103 0.0050 1.0000
12.000 1.2069 0.02454 0.01944 -0.0090 0.0049 1.0000
12.250 1.2038 0.02664 0.02160 -0.0070 0.0049 1.0000
12.500 1.2255 0.02689 0.02186 -0.0067 0.0047 1.0000
12.750 1.2314 0.02843 0.02345 -0.0055 0.0047 1.0000
13.000 1.2290 0.03071 0.02580 -0.0041 0.0048 1.0000
13.250 1.2393 0.03199 0.02712 -0.0034 0.0047 1.0000
13.500 1.2427 0.03390 0.02909 -0.0025 0.0046 1.0000
13.750 1.2497 0.03553 0.03076 -0.0018 0.0045 1.0000
14.000 1.2505 0.03774 0.03303 -0.0009 0.0045 1.0000
14.250 1.2588 0.03936 0.03470 -0.0005 0.0044 1.0000
14.500 1.2616 0.04151 0.03689 0.0001 0.0044 1.0000
14.750 1.2643 0.04373 0.03918 0.0006 0.0043 1.0000
15.000 1.2662 0.04607 0.04158 0.0011 0.0043 1.0000
15.250 1.2720 0.04810 0.04366 0.0013 0.0042 1.0000
15.500 1.2754 0.05040 0.04600 0.0015 0.0040 1.0000
15.750 1.2766 0.05293 0.04860 0.0018 0.0040 1.0000
16.000 1.2810 0.05527 0.05097 0.0016 0.0038 1.0000
16.250 1.2840 0.05772 0.05347 0.0016 0.0038 1.0000
16.500 1.2840 0.06046 0.05628 0.0019 0.0038 1.0000
16.750 1.2859 0.06326 0.05912 0.0014 0.0037 1.0000
17.000 1.2874 0.06592 0.06185 0.0014 0.0038 1.0000
17.250 1.2877 0.06887 0.06486 0.0011 0.0037 1.0000
17.500 1.2860 0.07178 0.06778 0.0012 0.0035 1.0000
17.750 1.2861 0.07472 0.07079 0.0011 0.0035 1.0000
18.000 1.2864 0.07757 0.07369 0.0010 0.0034 1.0000
18.250 1.2858 0.08083 0.07702 0.0003 0.0034 1.0000
18.500 1.2853 0.08382 0.08008 0.0002 0.0034 1.0000
18.750 1.2833 0.08738 0.08372 -0.0006 0.0034 1.0000
19.000 1.2817 0.09024 0.08665 0.0000 0.0034 1.0000
19.250 1.2772 0.09429 0.09080 -0.0012 0.0034 1.0000
19.500 1.2737 0.09821 0.09480 -0.0025 0.0034 1.0000
19.750 1.2673 0.10233 0.09902 -0.0032 0.0034 1.0000
20.000 1.2612 0.10693 0.10371 -0.0051 0.0034 1.0000
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