Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Reynolds number: 1,000,000 Max Cl/Cd: 74.55 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-tip-ns-1000000.txt Download as CSV file: xf-prandtl-d-tip-ns-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Prandtl-D tip - NASA Preliminary Research Aerody
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8028 0.14383 0.14212 0.0226 1.0000 0.0040
-15.500 -0.8115 0.13651 0.13477 0.0195 1.0000 0.0039
-15.250 -0.8393 0.12464 0.12283 0.0141 1.0000 0.0038
-15.000 -0.8472 0.11818 0.11633 0.0111 1.0000 0.0038
-14.750 -0.8602 0.11062 0.10874 0.0076 1.0000 0.0038
-14.500 -0.8842 0.10094 0.09899 0.0027 1.0000 0.0037
-14.250 -0.8821 0.09709 0.09511 0.0009 1.0000 0.0037
-14.000 -0.9213 0.08488 0.08279 -0.0057 1.0000 0.0036
-13.750 -0.9229 0.07981 0.07767 -0.0087 1.0000 0.0037
-13.500 -0.9698 0.06626 0.06392 -0.0173 1.0000 0.0036
-13.250 -0.9936 0.05725 0.05474 -0.0238 1.0000 0.0036
-13.000 -1.0025 0.05145 0.04880 -0.0282 1.0000 0.0036
-12.750 -1.0297 0.04374 0.04086 -0.0334 1.0000 0.0035
-12.500 -1.0392 0.03967 0.03662 -0.0352 1.0000 0.0035
-12.250 -1.0528 0.03594 0.03270 -0.0352 1.0000 0.0036
-12.000 -1.0573 0.03369 0.03030 -0.0340 1.0000 0.0036
-11.750 -1.0731 0.03085 0.02724 -0.0306 1.0000 0.0035
-11.500 -1.0750 0.02934 0.02560 -0.0273 1.0000 0.0036
-11.250 -1.0758 0.02772 0.02381 -0.0238 1.0000 0.0036
-11.000 -1.0674 0.02642 0.02237 -0.0216 1.0000 0.0036
-10.750 -1.0583 0.02503 0.02081 -0.0194 1.0000 0.0037
-10.500 -1.0701 0.02120 0.01654 -0.0143 1.0000 0.0040
-10.250 -1.0630 0.01933 0.01446 -0.0115 1.0000 0.0043
-10.000 -1.0465 0.01842 0.01346 -0.0098 1.0000 0.0046
-9.750 -1.0291 0.01757 0.01252 -0.0083 1.0000 0.0048
-9.500 -1.0100 0.01690 0.01178 -0.0069 1.0000 0.0050
-9.250 -0.9905 0.01626 0.01107 -0.0056 1.0000 0.0053
-9.000 -0.9710 0.01562 0.01035 -0.0042 1.0000 0.0056
-8.750 -0.9516 0.01496 0.00961 -0.0027 1.0000 0.0058
-8.500 -0.9317 0.01436 0.00893 -0.0013 1.0000 0.0061
-8.250 -0.9109 0.01385 0.00835 0.0000 1.0000 0.0064
-8.000 -0.8895 0.01341 0.00783 0.0012 1.0000 0.0066
-7.750 -0.8727 0.01243 0.00669 0.0033 1.0000 0.0080
-7.500 -0.8521 0.01193 0.00619 0.0047 1.0000 0.0100
-7.250 -0.8295 0.01169 0.00594 0.0057 1.0000 0.0116
-7.000 -0.8104 0.01105 0.00529 0.0074 1.0000 0.0170
-6.750 -0.7882 0.01080 0.00502 0.0085 1.0000 0.0189
-6.500 -0.7680 0.01035 0.00458 0.0100 1.0000 0.0252
-6.250 -0.7465 0.01008 0.00431 0.0113 1.0000 0.0291
-6.000 -0.7261 0.00972 0.00399 0.0128 1.0000 0.0386
-5.750 -0.7056 0.00940 0.00370 0.0142 1.0000 0.0491
-5.500 -0.6852 0.00910 0.00345 0.0156 1.0000 0.0615
-5.250 -0.6576 0.00877 0.00321 0.0155 0.9991 0.0809
-5.000 -0.6229 0.00843 0.00298 0.0138 0.9970 0.1037
-4.750 -0.5878 0.00811 0.00278 0.0121 0.9947 0.1287
-4.500 -0.5542 0.00782 0.00258 0.0107 0.9919 0.1518
-4.250 -0.5203 0.00752 0.00238 0.0093 0.9886 0.1792
-4.000 -0.4850 0.00724 0.00222 0.0075 0.9858 0.2075
-3.750 -0.4502 0.00698 0.00206 0.0059 0.9827 0.2357
-3.500 -0.4175 0.00673 0.00191 0.0048 0.9776 0.2623
-3.250 -0.3817 0.00647 0.00176 0.0030 0.9740 0.2947
-3.000 -0.3489 0.00622 0.00162 0.0020 0.9673 0.3266
-2.750 -0.3141 0.00599 0.00150 0.0004 0.9603 0.3595
-2.500 -0.2825 0.00578 0.00139 -0.0003 0.9496 0.3909
-2.250 -0.2518 0.00561 0.00129 -0.0009 0.9361 0.4209
-2.000 -0.2236 0.00542 0.00118 -0.0009 0.9182 0.4581
-1.750 -0.1976 0.00528 0.00111 -0.0003 0.8970 0.4927
-1.500 -0.1721 0.00518 0.00104 0.0004 0.8749 0.5243
-1.250 -0.1471 0.00511 0.00098 0.0012 0.8498 0.5529
-1.000 -0.1223 0.00505 0.00093 0.0020 0.8234 0.5833
-0.750 -0.0977 0.00502 0.00089 0.0028 0.7959 0.6122
-0.500 -0.0733 0.00499 0.00087 0.0037 0.7682 0.6428
-0.250 -0.0491 0.00496 0.00085 0.0047 0.7397 0.6752
0.000 -0.0246 0.00496 0.00084 0.0056 0.7106 0.7020
0.250 -0.0003 0.00494 0.00084 0.0064 0.6835 0.7324
0.500 0.0239 0.00493 0.00085 0.0074 0.6556 0.7652
0.750 0.0480 0.00494 0.00087 0.0084 0.6254 0.7958
1.000 0.0724 0.00495 0.00090 0.0093 0.5968 0.8265
1.250 0.0974 0.00497 0.00093 0.0101 0.5697 0.8559
1.500 0.1233 0.00502 0.00098 0.0107 0.5393 0.8849
1.750 0.1517 0.00510 0.00105 0.0107 0.5094 0.9106
2.000 0.1846 0.00524 0.00112 0.0097 0.4752 0.9332
2.250 0.2242 0.00545 0.00122 0.0071 0.4348 0.9483
2.500 0.2659 0.00569 0.00134 0.0039 0.3959 0.9562
2.750 0.3032 0.00591 0.00145 0.0019 0.3648 0.9629
3.000 0.3363 0.00616 0.00159 0.0007 0.3320 0.9703
3.250 0.3692 0.00641 0.00173 -0.0004 0.2995 0.9763
3.500 0.4023 0.00666 0.00188 -0.0016 0.2705 0.9820
3.750 0.4360 0.00693 0.00203 -0.0029 0.2398 0.9861
4.000 0.4716 0.00719 0.00218 -0.0047 0.2123 0.9892
4.500 0.5403 0.00775 0.00252 -0.0078 0.1572 0.9951
4.750 0.5759 0.00801 0.00270 -0.0096 0.1323 0.9972
5.000 0.6115 0.00828 0.00288 -0.0114 0.1102 0.9992
5.250 0.6395 0.00859 0.00309 -0.0117 0.0882 1.0000
5.500 0.6613 0.00887 0.00330 -0.0105 0.0719 1.0000
5.750 0.6830 0.00920 0.00355 -0.0094 0.0559 1.0000
6.000 0.7046 0.00955 0.00382 -0.0082 0.0420 1.0000
6.250 0.7269 0.00985 0.00410 -0.0071 0.0337 1.0000
6.500 0.7491 0.01020 0.00445 -0.0060 0.0266 1.0000
6.750 0.7715 0.01053 0.00475 -0.0050 0.0220 1.0000
7.000 0.7934 0.01094 0.00519 -0.0038 0.0174 1.0000
7.250 0.8162 0.01124 0.00550 -0.0029 0.0148 1.0000
7.500 0.8368 0.01186 0.00614 -0.0015 0.0105 1.0000
7.750 0.8593 0.01220 0.00649 -0.0005 0.0087 1.0000
8.000 0.8801 0.01279 0.00711 0.0008 0.0071 1.0000
8.250 0.8977 0.01378 0.00826 0.0027 0.0061 1.0000
8.500 0.9191 0.01426 0.00880 0.0038 0.0059 1.0000
8.750 0.9393 0.01488 0.00953 0.0052 0.0057 1.0000
9.000 0.9595 0.01549 0.01021 0.0065 0.0055 1.0000
9.250 0.9787 0.01619 0.01101 0.0079 0.0052 1.0000
9.500 0.9975 0.01693 0.01183 0.0094 0.0050 1.0000
9.750 1.0158 0.01770 0.01270 0.0109 0.0048 1.0000
10.000 1.0333 0.01854 0.01364 0.0124 0.0046 1.0000
10.250 1.0499 0.01944 0.01465 0.0141 0.0045 1.0000
10.500 1.0685 0.02008 0.01534 0.0153 0.0042 1.0000
10.750 1.0839 0.02104 0.01639 0.0170 0.0041 1.0000
11.000 1.0961 0.02226 0.01775 0.0190 0.0039 1.0000
11.250 1.0896 0.02526 0.02105 0.0232 0.0035 1.0000
11.500 1.0764 0.02862 0.02478 0.0276 0.0034 1.0000
11.750 1.0654 0.03082 0.02719 0.0320 0.0033 1.0000
12.000 1.0611 0.03273 0.02925 0.0347 0.0033 1.0000
12.250 1.0678 0.03394 0.03056 0.0359 0.0032 1.0000
12.500 1.0459 0.03833 0.03519 0.0363 0.0033 1.0000
12.750 1.0410 0.04169 0.03870 0.0351 0.0033 1.0000
13.000 1.0266 0.04711 0.04430 0.0317 0.0033 1.0000
13.250 1.0005 0.05538 0.05279 0.0258 0.0034 1.0000
13.500 0.9712 0.06540 0.06302 0.0185 0.0034 1.0000
13.750 0.9537 0.07354 0.07128 0.0130 0.0033 1.0000
14.500 0.9305 0.09125 0.08917 0.0031 0.0035 1.0000
14.750 0.9058 0.10073 0.09873 -0.0019 0.0035 1.0000
15.000 0.8797 0.11080 0.10887 -0.0070 0.0035 1.0000
15.250 0.8818 0.11479 0.11289 -0.0087 0.0036 1.0000
15.500 0.8808 0.11959 0.11773 -0.0109 0.0038 1.0000
15.750 0.8318 0.13624 0.13447 -0.0187 0.0037 1.0000
19.000 0.5899 0.20611 0.20463 -0.0464 0.0062 1.0000
19.250 0.5948 0.20957 0.20809 -0.0483 0.0062 1.0000
19.500 0.5997 0.21310 0.21162 -0.0501 0.0061 1.0000
19.750 0.6048 0.21644 0.21497 -0.0520 0.0061 1.0000
20.000 0.6098 0.21991 0.21845 -0.0539 0.0061 1.0000
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Polar data table (+)
Polar graphs
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