FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-150/20 (fx78k150-il) Reynolds number: 500,000 Max Cl/Cd: 114.73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k150-il-500000.txt Download as CSV file: xf-fx78k150-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-150/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.0864 0.10475 0.10143 -0.0955 0.7414 0.0234
-12.750 -0.0846 0.10111 0.09780 -0.0972 0.7408 0.0234
-12.500 -0.0905 0.09545 0.09216 -0.0989 0.7402 0.0239
-12.250 -0.0881 0.09186 0.08856 -0.1001 0.7394 0.0240
-12.000 -0.0867 0.08807 0.08477 -0.1014 0.7388 0.0241
-11.750 -0.0895 0.08343 0.08014 -0.1032 0.7382 0.0240
-11.500 -0.0753 0.08271 0.07939 -0.1028 0.7373 0.0251
-11.250 -0.2891 0.05359 0.05014 -0.1297 0.7419 0.0133
-11.000 -0.3473 0.04387 0.04015 -0.1353 0.7405 0.0135
-10.750 -0.3674 0.04065 0.03675 -0.1336 0.7390 0.0134
-10.500 -0.3952 0.03737 0.03325 -0.1297 0.7377 0.0134
-10.250 -0.4125 0.03524 0.03093 -0.1250 0.7366 0.0135
-10.000 -0.4335 0.03300 0.02845 -0.1191 0.7355 0.0136
-9.750 -0.4410 0.03083 0.02599 -0.1148 0.7344 0.0135
-9.500 -0.4460 0.02852 0.02347 -0.1109 0.7333 0.0140
-9.250 -0.4425 0.02657 0.02128 -0.1078 0.7322 0.0142
-9.000 -0.4308 0.02544 0.02000 -0.1058 0.7310 0.0144
-8.750 -0.4122 0.02528 0.01982 -0.1047 0.7296 0.0152
-8.500 -0.3956 0.02457 0.01898 -0.1032 0.7281 0.0161
-8.250 -0.3822 0.02287 0.01700 -0.1012 0.7268 0.0164
-8.000 -0.3629 0.02218 0.01612 -0.1000 0.7257 0.0174
-7.750 -0.3435 0.02120 0.01493 -0.0988 0.7247 0.0177
-7.500 -0.3273 0.01912 0.01261 -0.0972 0.7237 0.0185
-7.250 -0.3059 0.01858 0.01205 -0.0965 0.7228 0.0199
-7.000 -0.2832 0.01816 0.01154 -0.0958 0.7219 0.0214
-6.750 -0.2595 0.01778 0.01106 -0.0952 0.7209 0.0229
-6.500 -0.2389 0.01697 0.01015 -0.0942 0.7200 0.0251
-6.250 -0.2163 0.01672 0.00991 -0.0935 0.7187 0.0273
-6.000 -0.1933 0.01645 0.00959 -0.0929 0.7175 0.0296
-5.750 -0.1724 0.01590 0.00900 -0.0919 0.7162 0.0327
-5.500 -0.1493 0.01566 0.00877 -0.0913 0.7149 0.0361
-5.250 -0.1252 0.01548 0.00854 -0.0908 0.7136 0.0391
-5.000 -0.1038 0.01497 0.00800 -0.0898 0.7123 0.0431
-4.750 -0.0796 0.01474 0.00776 -0.0893 0.7110 0.0476
-4.500 -0.0542 0.01462 0.00759 -0.0891 0.7099 0.0519
-4.250 -0.0317 0.01423 0.00721 -0.0883 0.7089 0.0589
-4.000 -0.0064 0.01410 0.00702 -0.0880 0.7081 0.0640
-3.750 0.0167 0.01378 0.00672 -0.0873 0.7072 0.0736
-3.500 0.0409 0.01358 0.00652 -0.0868 0.7063 0.0850
-3.250 0.0649 0.01343 0.00640 -0.0863 0.7054 0.1009
-3.000 0.0862 0.01324 0.00636 -0.0854 0.7039 0.1309
-2.750 0.1060 0.01298 0.00634 -0.0842 0.7021 0.1889
-2.500 0.1245 0.01263 0.00634 -0.0829 0.7005 0.2780
-2.250 0.1407 0.01217 0.00631 -0.0811 0.6990 0.3970
-2.000 0.1490 0.01145 0.00623 -0.0775 0.6976 0.5734
-1.750 0.1569 0.01095 0.00644 -0.0730 0.6962 0.7641
-1.500 0.1792 0.01114 0.00666 -0.0716 0.6950 0.8174
-1.250 0.2025 0.01127 0.00672 -0.0706 0.6940 0.8367
-1.000 0.2276 0.01140 0.00682 -0.0699 0.6932 0.8500
-0.750 0.2541 0.01155 0.00693 -0.0694 0.6923 0.8617
-0.500 0.2804 0.01169 0.00705 -0.0690 0.6915 0.8718
-0.250 0.3016 0.01190 0.00723 -0.0677 0.6901 0.8805
0.000 0.3233 0.01213 0.00753 -0.0665 0.6876 0.8902
0.250 0.3451 0.01232 0.00774 -0.0652 0.6857 0.9011
0.500 0.3675 0.01241 0.00784 -0.0640 0.6840 0.9123
0.750 0.3905 0.01246 0.00789 -0.0628 0.6826 0.9231
1.000 0.4199 0.01246 0.00790 -0.0629 0.6814 0.9341
1.250 0.4484 0.01243 0.00785 -0.0631 0.6804 0.9411
1.500 0.4808 0.01239 0.00778 -0.0642 0.6795 0.9443
1.750 0.5103 0.01235 0.00771 -0.0649 0.6786 0.9464
2.000 0.5387 0.01231 0.00764 -0.0653 0.6777 0.9486
2.250 0.5650 0.01233 0.00764 -0.0653 0.6767 0.9509
2.500 0.5814 0.01257 0.00798 -0.0637 0.6730 0.9540
2.750 0.6098 0.01264 0.00807 -0.0643 0.6708 0.9555
3.000 0.6398 0.01264 0.00809 -0.0652 0.6691 0.9569
3.250 0.6709 0.01260 0.00805 -0.0663 0.6676 0.9584
3.500 0.7017 0.01255 0.00802 -0.0672 0.6664 0.9598
3.750 0.7332 0.01244 0.00791 -0.0683 0.6653 0.9610
4.000 0.7648 0.01234 0.00781 -0.0693 0.6642 0.9624
4.250 0.7959 0.01228 0.00776 -0.0703 0.6632 0.9638
4.500 0.8169 0.01249 0.00807 -0.0696 0.6599 0.9664
4.750 0.8467 0.01260 0.00825 -0.0707 0.6569 0.9676
5.000 0.8798 0.01258 0.00830 -0.0722 0.6548 0.9687
5.250 0.9138 0.01253 0.00829 -0.0739 0.6532 0.9697
5.500 0.9529 0.01187 0.00762 -0.0760 0.6506 0.9700
5.750 0.9862 0.01111 0.00690 -0.0769 0.6420 0.9712
6.000 1.0240 0.01035 0.00609 -0.0787 0.6353 0.9716
6.250 1.0522 0.00993 0.00575 -0.0789 0.6227 0.9736
6.500 1.0811 0.00966 0.00551 -0.0794 0.6064 0.9756
6.750 1.1060 0.00964 0.00548 -0.0793 0.5697 0.9784
7.000 1.1009 0.01153 0.00669 -0.0752 0.4455 0.9866
7.250 1.0753 0.01409 0.00896 -0.0693 0.3843 1.0000
7.500 1.0532 0.01741 0.01195 -0.0654 0.3219 1.0000
7.750 1.0247 0.02114 0.01517 -0.0607 0.2334 1.0000
8.000 1.0001 0.02463 0.01812 -0.0564 0.1365 1.0000
8.250 0.9760 0.02818 0.02106 -0.0521 0.0365 1.0000
8.500 0.9842 0.02962 0.02247 -0.0507 0.0258 1.0000
8.750 0.9947 0.03092 0.02378 -0.0497 0.0217 1.0000
9.000 1.0009 0.03261 0.02555 -0.0482 0.0190 1.0000
9.250 1.0139 0.03382 0.02679 -0.0474 0.0168 1.0000
9.500 1.0250 0.03517 0.02819 -0.0465 0.0161 1.0000
9.750 1.0351 0.03664 0.02971 -0.0456 0.0158 1.0000
10.000 1.0385 0.03865 0.03176 -0.0441 0.0147 1.0000
10.250 1.0422 0.04066 0.03385 -0.0426 0.0139 1.0000
10.500 1.0478 0.04250 0.03574 -0.0412 0.0142 1.0000
10.750 1.0578 0.04399 0.03729 -0.0402 0.0140 1.0000
11.000 1.0691 0.04540 0.03876 -0.0393 0.0129 1.0000
11.250 1.0788 0.04688 0.04031 -0.0381 0.0127 1.0000
11.500 1.0897 0.04820 0.04168 -0.0370 0.0127 1.0000
11.750 1.1029 0.04945 0.04297 -0.0364 0.0120 1.0000
12.000 1.1154 0.05078 0.04430 -0.0359 0.0112 1.0000
12.250 1.1301 0.05156 0.04515 -0.0339 0.0115 1.0000
12.500 1.1434 0.05271 0.04629 -0.0332 0.0108 1.0000
12.750 1.1751 0.05230 0.04593 -0.0308 0.0103 1.0000
13.000 1.1880 0.05360 0.04730 -0.0304 0.0107 1.0000
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