GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 50,000 Max Cl/Cd: 40.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe374-il-50000-n5.txt Download as CSV file: xf-goe374-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3263 0.10483 0.09824 -0.0206 1.0000 0.0484
-7.750 -0.3289 0.10364 0.09718 -0.0219 1.0000 0.0491
-7.500 -0.3280 0.10226 0.09590 -0.0246 1.0000 0.0495
-7.250 -0.3240 0.10074 0.09446 -0.0280 1.0000 0.0498
-7.000 -0.3184 0.09563 0.08946 -0.0263 1.0000 0.0508
-6.750 -0.3122 0.09103 0.08491 -0.0233 1.0000 0.0529
-6.500 -0.3074 0.08815 0.08210 -0.0233 1.0000 0.0547
-6.250 -0.3024 0.08547 0.07949 -0.0239 1.0000 0.0570
-6.000 -0.2967 0.08295 0.07704 -0.0253 1.0000 0.0599
-5.750 -0.2867 0.08127 0.07536 -0.0294 1.0000 0.0630
-5.500 -0.2704 0.08042 0.07439 -0.0353 1.0000 0.0641
-5.250 -0.2744 0.07479 0.06902 -0.0294 1.0000 0.0669
-5.000 -0.2681 0.07201 0.06628 -0.0287 1.0000 0.0716
-4.750 -0.2438 0.07114 0.06518 -0.0359 1.0000 0.0784
-4.500 -0.2466 0.06648 0.06071 -0.0312 1.0000 0.0822
-4.250 -0.2205 0.06570 0.05962 -0.0368 1.0000 0.0920
-4.000 -0.2215 0.06105 0.05522 -0.0330 1.0000 0.0958
-3.750 -0.2021 0.05883 0.05284 -0.0355 1.0000 0.1072
-3.500 -0.1871 0.05637 0.05030 -0.0364 1.0000 0.1211
-3.250 -0.1750 0.05327 0.04723 -0.0361 0.9993 0.1367
-3.000 -0.1394 0.04939 0.04331 -0.0407 0.9881 0.1812
-1.750 0.1095 0.03374 0.02518 -0.0631 0.9325 0.0748
-1.500 0.1518 0.03139 0.02236 -0.0655 0.9210 0.0722
-1.250 0.1968 0.02931 0.01972 -0.0677 0.9103 0.0673
-1.000 0.2372 0.02759 0.01763 -0.0695 0.8977 0.0710
-0.500 0.3143 0.02486 0.01413 -0.0717 0.8695 0.0726
-0.250 0.3535 0.02381 0.01272 -0.0728 0.8545 0.0748
0.000 0.3881 0.02293 0.01163 -0.0733 0.8367 0.0816
0.250 0.4213 0.02218 0.01068 -0.0734 0.8183 0.0830
0.500 0.4536 0.02159 0.00989 -0.0735 0.7997 0.0845
0.750 0.4833 0.02117 0.00929 -0.0731 0.7789 0.0865
1.000 0.5124 0.02087 0.00879 -0.0727 0.7577 0.0891
1.250 0.5414 0.02064 0.00838 -0.0722 0.7363 0.0930
1.500 0.5695 0.02045 0.00808 -0.0717 0.7144 0.1007
1.750 0.5977 0.02017 0.00787 -0.0712 0.6938 0.1328
2.250 0.6589 0.01882 0.00762 -0.0713 0.6529 1.0000
2.500 0.6845 0.01914 0.00769 -0.0705 0.6331 1.0000
2.750 0.7102 0.01949 0.00784 -0.0698 0.6142 1.0000
3.000 0.7358 0.01986 0.00804 -0.0691 0.5965 1.0000
3.250 0.7613 0.02026 0.00829 -0.0684 0.5796 1.0000
3.500 0.7861 0.02068 0.00865 -0.0678 0.5628 1.0000
3.750 0.8107 0.02111 0.00903 -0.0671 0.5467 1.0000
4.000 0.8353 0.02155 0.00944 -0.0665 0.5311 1.0000
4.250 0.8598 0.02199 0.00986 -0.0658 0.5163 1.0000
4.500 0.8841 0.02245 0.01036 -0.0651 0.5017 1.0000
4.750 0.9083 0.02291 0.01083 -0.0644 0.4875 1.0000
5.000 0.9319 0.02338 0.01132 -0.0636 0.4723 1.0000
5.250 0.9548 0.02384 0.01185 -0.0626 0.4555 1.0000
5.500 0.9772 0.02429 0.01231 -0.0615 0.4378 1.0000
5.750 0.9995 0.02477 0.01279 -0.0605 0.4205 1.0000
6.000 1.0218 0.02530 0.01336 -0.0595 0.4042 1.0000
6.250 1.0438 0.02591 0.01414 -0.0585 0.3885 1.0000
6.500 1.0656 0.02654 0.01492 -0.0576 0.3734 1.0000
6.750 1.0870 0.02720 0.01576 -0.0566 0.3582 1.0000
7.000 1.1077 0.02788 0.01664 -0.0555 0.3424 1.0000
7.250 1.1279 0.02859 0.01755 -0.0544 0.3265 1.0000
7.500 1.1478 0.02933 0.01856 -0.0532 0.3110 1.0000
7.750 1.1679 0.03016 0.01960 -0.0521 0.2969 1.0000
8.000 1.1856 0.03089 0.02053 -0.0506 0.2800 1.0000
8.250 1.1985 0.03136 0.02104 -0.0486 0.2572 1.0000
8.500 1.2120 0.03214 0.02201 -0.0469 0.2365 1.0000
9.000 1.2315 0.03398 0.02404 -0.0429 0.1879 1.0000
9.250 1.2419 0.03519 0.02543 -0.0411 0.1662 1.0000
9.500 1.2499 0.03661 0.02698 -0.0391 0.1467 1.0000
9.750 1.2521 0.03845 0.02883 -0.0368 0.1201 1.0000
10.000 1.2491 0.04076 0.03108 -0.0343 0.0761 1.0000
10.250 1.2354 0.04414 0.03406 -0.0321 0.0474 1.0000
10.500 1.2252 0.04759 0.03747 -0.0307 0.0394 1.0000
10.750 1.2157 0.05130 0.04128 -0.0300 0.0356 1.0000
11.000 1.2060 0.05534 0.04546 -0.0301 0.0339 1.0000
11.250 1.1965 0.05972 0.05001 -0.0308 0.0328 1.0000
11.500 1.1864 0.06454 0.05504 -0.0321 0.0317 1.0000
11.750 1.1767 0.06954 0.06024 -0.0337 0.0310 1.0000
12.000 1.1674 0.07466 0.06556 -0.0354 0.0305 1.0000
12.250 1.1577 0.07997 0.07105 -0.0373 0.0300 1.0000
12.500 1.1484 0.08535 0.07659 -0.0393 0.0295 1.0000
12.750 1.1391 0.09078 0.08217 -0.0413 0.0289 1.0000
13.000 1.1303 0.09618 0.08771 -0.0433 0.0284 1.0000
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Polar data table (+)
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