GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 50,000 Max Cl/Cd: 39.67 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe101-il-50000.txt Download as CSV file: xf-goe101-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3874 0.10211 0.09546 -0.0132 1.0000 0.1418
-7.750 -0.3900 0.10033 0.09379 -0.0145 1.0000 0.1481
-7.500 -0.4016 0.10026 0.09388 -0.0195 1.0000 0.1501
-7.250 -0.3823 0.09409 0.08771 -0.0150 1.0000 0.1608
-7.000 -0.3906 0.09391 0.08765 -0.0223 1.0000 0.1645
-6.750 -0.3751 0.08842 0.08220 -0.0175 1.0000 0.1761
-6.250 -0.3676 0.08274 0.07665 -0.0212 1.0000 0.1944
-6.000 -0.3627 0.08042 0.07438 -0.0236 1.0000 0.2078
-5.750 -0.3552 0.07670 0.07074 -0.0216 1.0000 0.2231
-5.250 -0.3440 0.07104 0.06523 -0.0198 1.0000 0.2660
-5.000 -0.3393 0.06856 0.06283 -0.0185 1.0000 0.2942
-4.750 -0.3351 0.06565 0.06002 -0.0150 1.0000 0.3233
-4.500 0.0078 0.03875 0.03200 -0.0224 1.0000 1.0000
-4.250 0.0190 0.03688 0.03020 -0.0233 1.0000 1.0000
-4.000 0.0301 0.03510 0.02848 -0.0242 1.0000 1.0000
-3.750 0.0320 0.03399 0.02747 -0.0227 1.0000 0.9960
-3.500 -0.0189 0.03596 0.02971 -0.0092 1.0000 0.9604
-3.250 -0.0673 0.03726 0.03130 0.0023 1.0000 0.9214
-3.000 -0.1139 0.03802 0.03236 0.0124 1.0000 0.8859
-2.750 -0.1603 0.03843 0.03309 0.0217 1.0000 0.8570
-2.500 -0.2072 0.03867 0.03363 0.0313 1.0000 0.8414
-1.750 -0.0612 0.03189 0.02357 -0.0442 1.0000 0.1991
-1.500 -0.0332 0.03083 0.02180 -0.0448 1.0000 0.1781
-1.250 -0.0118 0.02960 0.02033 -0.0448 1.0000 0.1684
-1.000 0.0248 0.02868 0.01896 -0.0473 0.9941 0.1598
-0.750 0.0838 0.02754 0.01733 -0.0533 0.9770 0.1558
-0.500 0.1394 0.02679 0.01620 -0.0585 0.9598 0.1621
-0.250 0.1966 0.02612 0.01519 -0.0636 0.9436 0.1648
0.000 0.2499 0.02541 0.01444 -0.0682 0.9279 0.1741
0.250 0.3005 0.02486 0.01389 -0.0724 0.9123 0.1950
0.500 0.3552 0.02222 0.01342 -0.0770 0.8993 1.0000
0.750 0.4032 0.02259 0.01309 -0.0801 0.8842 1.0000
1.000 0.4395 0.02306 0.01323 -0.0818 0.8680 1.0000
1.250 0.4754 0.02351 0.01347 -0.0834 0.8532 1.0000
1.500 0.5103 0.02397 0.01379 -0.0847 0.8396 1.0000
1.750 0.5458 0.02439 0.01409 -0.0860 0.8273 1.0000
2.000 0.5733 0.02503 0.01467 -0.0862 0.8141 1.0000
2.250 0.5986 0.02576 0.01536 -0.0862 0.8014 1.0000
2.500 0.6231 0.02655 0.01611 -0.0860 0.7892 1.0000
2.750 0.6479 0.02736 0.01693 -0.0859 0.7779 1.0000
3.000 0.6752 0.02807 0.01768 -0.0859 0.7672 1.0000
3.250 0.7046 0.02866 0.01831 -0.0860 0.7569 1.0000
3.500 0.7246 0.02970 0.01940 -0.0854 0.7447 1.0000
3.750 0.7464 0.03065 0.02041 -0.0847 0.7323 1.0000
4.000 0.7712 0.03129 0.02113 -0.0838 0.7184 1.0000
4.250 0.7977 0.03170 0.02168 -0.0827 0.7034 1.0000
4.500 0.8241 0.03206 0.02214 -0.0814 0.6881 1.0000
4.750 0.8492 0.03255 0.02275 -0.0801 0.6732 1.0000
5.000 0.8735 0.03314 0.02348 -0.0789 0.6585 1.0000
5.250 0.8984 0.03365 0.02421 -0.0775 0.6435 1.0000
5.500 0.9246 0.03403 0.02476 -0.0760 0.6280 1.0000
5.750 0.9411 0.03519 0.02613 -0.0744 0.6090 1.0000
6.000 0.9667 0.03534 0.02648 -0.0723 0.5892 1.0000
6.250 0.9922 0.03521 0.02658 -0.0697 0.5662 1.0000
6.500 1.0222 0.03431 0.02582 -0.0667 0.5410 1.0000
6.750 1.0503 0.03360 0.02525 -0.0638 0.5143 1.0000
7.000 1.0735 0.03367 0.02553 -0.0613 0.4865 1.0000
7.250 1.0956 0.03261 0.02465 -0.0577 0.4485 1.0000
7.500 1.1160 0.02979 0.02173 -0.0529 0.3966 1.0000
7.750 1.1246 0.02835 0.02027 -0.0483 0.3303 1.0000
8.000 1.1182 0.02991 0.02085 -0.0431 0.2203 1.0000
8.250 1.1112 0.03407 0.02409 -0.0391 0.1487 1.0000
8.500 1.1194 0.03682 0.02664 -0.0366 0.1194 1.0000
8.750 1.1388 0.03941 0.02914 -0.0349 0.1044 1.0000
9.000 1.1673 0.04251 0.03233 -0.0339 0.0948 1.0000
9.250 1.1937 0.04595 0.03566 -0.0335 0.0867 1.0000
9.500 1.2086 0.04924 0.03956 -0.0319 0.0827 1.0000
9.750 1.2226 0.05321 0.04400 -0.0304 0.0807 1.0000
10.000 1.2303 0.05745 0.04872 -0.0288 0.0801 1.0000
10.250 1.2304 0.06191 0.05366 -0.0270 0.0802 1.0000
10.500 1.2233 0.06642 0.05861 -0.0253 0.0807 1.0000
10.750 1.2098 0.07096 0.06351 -0.0236 0.0815 1.0000
11.000 1.1906 0.07522 0.06803 -0.0220 0.0822 1.0000
11.250 1.1682 0.07988 0.07290 -0.0216 0.0830 1.0000
11.500 1.1448 0.08517 0.07837 -0.0228 0.0838 1.0000
11.750 1.1221 0.09125 0.08457 -0.0253 0.0848 1.0000
12.000 1.1009 0.09804 0.09145 -0.0287 0.0857 1.0000
12.250 1.0860 0.10506 0.09852 -0.0319 0.0867 1.0000
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Polar data table (+)
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