Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Xfoil prediction polar at RE=5,000,000 Ncrit=9
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Airfoil: Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Reynolds number: 5,000,000 Max Cl/Cd: 128.79 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-root-ns-5000000.txt Download as CSV file: xf-prandtl-d-root-ns-5000000.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 = 5.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.4005 0.03459 0.03221 -0.0537 0.8863 0.0036
-15.750 -1.4015 0.03312 0.03068 -0.0518 0.8800 0.0036
-15.500 -1.4153 0.03111 0.02855 -0.0483 0.8727 0.0036
-15.250 -1.4202 0.02979 0.02715 -0.0445 0.8668 0.0036
-15.000 -1.4167 0.02864 0.02591 -0.0418 0.8602 0.0036
-14.750 -1.4074 0.02747 0.02466 -0.0400 0.8562 0.0037
-14.500 -1.3966 0.02629 0.02340 -0.0382 0.8509 0.0037
-14.250 -1.3828 0.02528 0.02230 -0.0367 0.8444 0.0037
-14.000 -1.3666 0.02441 0.02137 -0.0355 0.8399 0.0037
-13.750 -1.3486 0.02366 0.02056 -0.0343 0.8333 0.0037
-13.500 -1.3324 0.02267 0.01947 -0.0330 0.8268 0.0037
-13.250 -1.3130 0.02195 0.01870 -0.0320 0.8199 0.0037
-13.000 -1.2922 0.02136 0.01805 -0.0312 0.8119 0.0037
-12.750 -1.2716 0.02070 0.01733 -0.0303 0.8039 0.0038
-12.500 -1.2513 0.01997 0.01652 -0.0293 0.7957 0.0038
-12.250 -1.2299 0.01934 0.01581 -0.0285 0.7871 0.0038
-12.000 -1.2157 0.01778 0.01403 -0.0268 0.7787 0.0039
-11.750 -1.1974 0.01667 0.01275 -0.0255 0.7686 0.0042
-11.500 -1.1754 0.01598 0.01197 -0.0247 0.7608 0.0042
-11.250 -1.1524 0.01539 0.01131 -0.0239 0.7516 0.0044
-11.000 -1.1290 0.01484 0.01068 -0.0233 0.7435 0.0045
-10.750 -1.1044 0.01443 0.01022 -0.0227 0.7349 0.0046
-10.500 -1.0798 0.01401 0.00974 -0.0222 0.7263 0.0047
-10.250 -1.0549 0.01360 0.00927 -0.0217 0.7182 0.0047
-10.000 -1.0296 0.01323 0.00885 -0.0212 0.7095 0.0048
-9.750 -1.0042 0.01288 0.00846 -0.0208 0.7025 0.0049
-9.500 -0.9789 0.01249 0.00800 -0.0203 0.6944 0.0049
-9.250 -0.9531 0.01214 0.00761 -0.0199 0.6880 0.0050
-9.000 -0.9270 0.01185 0.00727 -0.0196 0.6809 0.0051
-8.750 -0.9009 0.01151 0.00688 -0.0192 0.6743 0.0051
-8.500 -0.8746 0.01123 0.00655 -0.0188 0.6684 0.0052
-8.250 -0.8482 0.01093 0.00621 -0.0185 0.6614 0.0053
-8.000 -0.8216 0.01066 0.00590 -0.0182 0.6572 0.0054
-7.750 -0.7949 0.01039 0.00560 -0.0179 0.6513 0.0054
-7.500 -0.7680 0.01014 0.00530 -0.0177 0.6453 0.0055
-7.250 -0.7410 0.00990 0.00503 -0.0174 0.6409 0.0055
-7.000 -0.7138 0.00968 0.00478 -0.0172 0.6356 0.0056
-6.750 -0.6866 0.00947 0.00454 -0.0170 0.6303 0.0056
-6.500 -0.6592 0.00926 0.00431 -0.0169 0.6266 0.0057
-6.250 -0.6325 0.00892 0.00390 -0.0165 0.6216 0.0061
-6.000 -0.6054 0.00867 0.00361 -0.0163 0.6158 0.0067
-5.750 -0.5778 0.00848 0.00342 -0.0161 0.6128 0.0070
-5.500 -0.5501 0.00831 0.00324 -0.0160 0.6086 0.0074
-5.250 -0.5222 0.00817 0.00308 -0.0159 0.6032 0.0077
-5.000 -0.4942 0.00803 0.00292 -0.0158 0.5994 0.0078
-4.750 -0.4662 0.00790 0.00279 -0.0158 0.5958 0.0080
-4.500 -0.4385 0.00770 0.00255 -0.0156 0.5913 0.0087
-4.250 -0.4106 0.00755 0.00239 -0.0156 0.5859 0.0096
-4.000 -0.3824 0.00742 0.00227 -0.0155 0.5835 0.0102
-3.750 -0.3542 0.00731 0.00215 -0.0155 0.5800 0.0105
-3.500 -0.3259 0.00722 0.00204 -0.0155 0.5756 0.0107
-3.250 -0.2977 0.00708 0.00189 -0.0155 0.5707 0.0116
-3.000 -0.2696 0.00694 0.00175 -0.0154 0.5685 0.0128
-2.750 -0.2412 0.00684 0.00165 -0.0154 0.5653 0.0136
-2.500 -0.2128 0.00676 0.00156 -0.0155 0.5612 0.0141
-2.250 -0.1844 0.00666 0.00144 -0.0155 0.5559 0.0154
-2.000 -0.1561 0.00654 0.00134 -0.0155 0.5538 0.0176
-1.750 -0.1276 0.00645 0.00125 -0.0155 0.5506 0.0195
-1.500 -0.0996 0.00631 0.00113 -0.0155 0.5469 0.0286
-1.250 -0.0717 0.00615 0.00105 -0.0154 0.5420 0.0461
-1.000 -0.0429 0.00611 0.00101 -0.0156 0.5393 0.0467
-0.750 -0.0142 0.00606 0.00095 -0.0157 0.5362 0.0489
-0.500 0.0144 0.00600 0.00090 -0.0158 0.5322 0.0530
-0.250 0.0429 0.00596 0.00085 -0.0159 0.5271 0.0560
0.000 0.0717 0.00591 0.00081 -0.0160 0.5244 0.0581
0.250 0.1003 0.00584 0.00078 -0.0161 0.5212 0.0663
0.500 0.1283 0.00572 0.00073 -0.0161 0.5171 0.0920
0.750 0.1566 0.00565 0.00070 -0.0162 0.5116 0.1115
1.000 0.1846 0.00553 0.00068 -0.0162 0.5091 0.1440
1.250 0.2128 0.00544 0.00066 -0.0163 0.5047 0.1711
1.500 0.2410 0.00538 0.00065 -0.0164 0.4983 0.1975
1.750 0.2692 0.00531 0.00064 -0.0164 0.4943 0.2260
2.000 0.2974 0.00524 0.00064 -0.0165 0.4901 0.2531
2.250 0.3254 0.00518 0.00065 -0.0166 0.4841 0.2872
2.500 0.3534 0.00512 0.00066 -0.0167 0.4783 0.3201
2.750 0.3813 0.00510 0.00068 -0.0168 0.4684 0.3546
3.000 0.4086 0.00502 0.00070 -0.0167 0.4589 0.4078
3.250 0.4359 0.00497 0.00074 -0.0167 0.4496 0.4545
3.500 0.4630 0.00493 0.00078 -0.0167 0.4386 0.5033
3.750 0.4892 0.00480 0.00082 -0.0164 0.4319 0.5768
4.000 0.5112 0.00451 0.00086 -0.0153 0.4214 0.7257
4.250 0.5229 0.00406 0.00096 -0.0118 0.3971 0.9504
4.500 0.5503 0.00434 0.00111 -0.0120 0.3602 0.9605
4.750 0.5760 0.00472 0.00130 -0.0118 0.3145 0.9662
5.000 0.6007 0.00525 0.00157 -0.0116 0.2541 0.9699
5.250 0.6288 0.00582 0.00188 -0.0122 0.1937 0.9748
5.500 0.6535 0.00641 0.00222 -0.0120 0.1340 0.9795
5.750 0.6752 0.00706 0.00260 -0.0112 0.0726 0.9832
6.000 0.7077 0.00759 0.00295 -0.0128 0.0320 0.9847
6.250 0.7406 0.00802 0.00328 -0.0143 0.0065 0.9855
6.500 0.7737 0.00824 0.00348 -0.0157 0.0056 0.9863
6.750 0.8081 0.00847 0.00370 -0.0174 0.0052 0.9871
7.000 0.8429 0.00872 0.00395 -0.0192 0.0050 0.9879
7.250 0.8764 0.00896 0.00417 -0.0208 0.0050 0.9887
7.500 0.9067 0.00919 0.00438 -0.0217 0.0049 0.9894
7.750 0.9347 0.00940 0.00459 -0.0220 0.0048 0.9900
8.000 0.9617 0.00963 0.00481 -0.0222 0.0047 0.9907
8.250 0.9881 0.00986 0.00503 -0.0223 0.0044 0.9914
8.500 1.0137 0.01012 0.00529 -0.0223 0.0043 0.9922
8.750 1.0372 0.01039 0.00556 -0.0218 0.0041 0.9932
9.000 1.0590 0.01068 0.00585 -0.0210 0.0038 0.9942
9.250 1.0869 0.01100 0.00618 -0.0215 0.0038 0.9944
9.500 1.1145 0.01135 0.00653 -0.0221 0.0036 0.9947
9.750 1.1389 0.01213 0.00740 -0.0225 0.0033 0.9951
10.000 1.1646 0.01266 0.00795 -0.0229 0.0033 0.9955
10.250 1.1902 0.01315 0.00846 -0.0233 0.0033 0.9960
10.500 1.2157 0.01363 0.00895 -0.0238 0.0032 0.9966
10.750 1.2408 0.01419 0.00953 -0.0242 0.0032 0.9973
11.000 1.2657 0.01473 0.01009 -0.0247 0.0032 0.9980
11.250 1.2893 0.01514 0.01049 -0.0250 0.0032 0.9988
11.500 1.3070 0.01597 0.01137 -0.0249 0.0032 0.9997
11.750 1.3165 0.01682 0.01225 -0.0231 0.0032 1.0000
12.000 1.3197 0.01752 0.01299 -0.0199 0.0031 1.0000
12.250 1.3187 0.01864 0.01417 -0.0165 0.0031 1.0000
12.500 1.3370 0.01887 0.01438 -0.0155 0.0030 1.0000
12.750 1.3438 0.01984 0.01539 -0.0135 0.0030 1.0000
13.000 1.3418 0.02154 0.01716 -0.0110 0.0030 1.0000
13.250 1.3551 0.02229 0.01792 -0.0099 0.0030 1.0000
13.500 1.3610 0.02362 0.01929 -0.0084 0.0030 1.0000
13.750 1.3712 0.02471 0.02041 -0.0074 0.0029 1.0000
14.000 1.3745 0.02642 0.02218 -0.0061 0.0029 1.0000
14.250 1.3883 0.02734 0.02311 -0.0056 0.0029 1.0000
14.500 1.3927 0.02908 0.02490 -0.0046 0.0029 1.0000
14.750 1.3959 0.03097 0.02685 -0.0037 0.0028 1.0000
15.000 1.3962 0.03318 0.02912 -0.0028 0.0029 1.0000
15.250 1.4082 0.03437 0.03033 -0.0025 0.0028 1.0000
15.500 1.4256 0.03508 0.03104 -0.0024 0.0026 1.0000
15.750 1.4204 0.03800 0.03404 -0.0016 0.0027 1.0000
16.000 1.4447 0.03807 0.03409 -0.0018 0.0025 1.0000
16.250 1.4415 0.04087 0.03696 -0.0013 0.0026 1.0000
16.500 1.4326 0.04439 0.04057 -0.0009 0.0026 1.0000
16.750 1.4569 0.04444 0.04060 -0.0011 0.0025 1.0000
17.000 1.4361 0.04935 0.04565 -0.0007 0.0025 1.0000
17.250 1.4396 0.05175 0.04808 -0.0008 0.0025 1.0000
17.500 1.4713 0.05095 0.04723 -0.0010 0.0024 1.0000
17.750 1.4716 0.05372 0.05005 -0.0011 0.0023 1.0000
18.000 1.4744 0.05623 0.05261 -0.0013 0.0023 1.0000
18.250 1.4691 0.05973 0.05619 -0.0016 0.0023 1.0000
18.500 1.4545 0.06455 0.06111 -0.0022 0.0024 1.0000
18.750 1.4610 0.06676 0.06335 -0.0026 0.0023 1.0000
19.000 1.4701 0.06863 0.06524 -0.0030 0.0022 1.0000
19.250 1.4733 0.07125 0.06789 -0.0035 0.0021 1.0000
19.500 1.4645 0.07555 0.07227 -0.0044 0.0022 1.0000
19.750 1.4627 0.07899 0.07576 -0.0052 0.0021 1.0000
20.000 1.4542 0.08339 0.08024 -0.0063 0.0022 1.0000
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