GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 50,000 Max Cl/Cd: 38.07 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe595-il-50000-n5.txt Download as CSV file: xf-goe595-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 595 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3888 0.10868 0.10176 -0.0339 1.0000 0.1070
-9.000 -0.4056 0.10702 0.10026 -0.0361 1.0000 0.1107
-8.500 -0.4133 0.09488 0.08822 -0.0403 1.0000 0.0560
-8.250 -0.4146 0.09189 0.08531 -0.0392 1.0000 0.0552
-8.000 -0.4218 0.08900 0.08252 -0.0384 1.0000 0.0546
-7.750 -0.4295 0.08610 0.07972 -0.0378 1.0000 0.0537
-7.500 -0.4366 0.08280 0.07650 -0.0378 1.0000 0.0528
-7.250 -0.4440 0.07928 0.07304 -0.0379 1.0000 0.0519
-7.000 -0.4504 0.07567 0.06945 -0.0380 1.0000 0.0508
-6.750 -0.4562 0.07163 0.06541 -0.0383 1.0000 0.0496
-6.500 -0.4606 0.06707 0.06076 -0.0389 1.0000 0.0482
-6.250 -0.4653 0.06067 0.05385 -0.0408 1.0000 0.0454
-6.000 -0.4601 0.05720 0.05025 -0.0399 1.0000 0.0450
-5.750 -0.4536 0.05346 0.04627 -0.0391 1.0000 0.0448
-5.500 -0.4445 0.04982 0.04234 -0.0384 1.0000 0.0446
-5.250 -0.4330 0.04624 0.03838 -0.0376 1.0000 0.0446
-5.000 -0.4187 0.04273 0.03423 -0.0368 1.0000 0.0453
-4.750 -0.4042 0.04026 0.03165 -0.0360 1.0000 0.0473
-4.500 -0.3871 0.03808 0.02918 -0.0351 1.0000 0.0496
-4.250 -0.3675 0.03551 0.02612 -0.0342 1.0000 0.0509
-4.000 -0.3460 0.03321 0.02332 -0.0333 1.0000 0.0523
-3.750 -0.3235 0.03134 0.02090 -0.0323 1.0000 0.0557
-3.500 -0.3024 0.02991 0.01929 -0.0314 1.0000 0.0601
-3.250 -0.2801 0.02858 0.01766 -0.0303 1.0000 0.0638
-3.000 -0.2549 0.02749 0.01619 -0.0296 0.9991 0.0693
-2.750 -0.2204 0.02649 0.01510 -0.0311 0.9942 0.0803
-2.500 -0.1856 0.02555 0.01399 -0.0325 0.9890 0.0902
-2.250 -0.1504 0.02482 0.01319 -0.0342 0.9832 0.1149
-2.000 -0.1129 0.02378 0.01245 -0.0365 0.9773 0.1852
-1.750 -0.0805 0.02231 0.01217 -0.0383 0.9695 0.4208
-1.500 -0.0144 0.02096 0.01208 -0.0441 0.9656 1.0000
-1.250 0.0253 0.02117 0.01182 -0.0468 0.9546 1.0000
-1.000 0.0615 0.02135 0.01161 -0.0487 0.9436 1.0000
-0.750 0.0973 0.02155 0.01150 -0.0506 0.9337 1.0000
-0.500 0.1366 0.02176 0.01144 -0.0531 0.9254 1.0000
-0.250 0.1673 0.02193 0.01138 -0.0540 0.9145 1.0000
0.000 0.1999 0.02211 0.01137 -0.0552 0.9043 1.0000
0.250 0.2403 0.02225 0.01133 -0.0577 0.8962 1.0000
0.500 0.2695 0.02239 0.01136 -0.0582 0.8843 1.0000
0.750 0.3000 0.02253 0.01140 -0.0588 0.8729 1.0000
1.000 0.3327 0.02263 0.01142 -0.0598 0.8617 1.0000
1.250 0.3698 0.02266 0.01138 -0.0615 0.8520 1.0000
1.500 0.4025 0.02269 0.01139 -0.0623 0.8404 1.0000
1.750 0.4323 0.02274 0.01143 -0.0625 0.8274 1.0000
2.250 0.4921 0.02279 0.01150 -0.0629 0.8008 1.0000
2.500 0.5222 0.02279 0.01155 -0.0630 0.7871 1.0000
2.750 0.5533 0.02270 0.01150 -0.0632 0.7723 1.0000
3.000 0.5862 0.02246 0.01133 -0.0633 0.7558 1.0000
3.250 0.6178 0.02217 0.01107 -0.0631 0.7363 1.0000
3.500 0.6461 0.02198 0.01093 -0.0623 0.7144 1.0000
3.750 0.6782 0.02177 0.01077 -0.0622 0.6943 1.0000
4.000 0.7035 0.02187 0.01094 -0.0613 0.6729 1.0000
4.250 0.7326 0.02190 0.01102 -0.0610 0.6530 1.0000
4.500 0.7587 0.02205 0.01128 -0.0602 0.6318 1.0000
4.750 0.7855 0.02222 0.01151 -0.0596 0.6107 1.0000
5.000 0.8115 0.02245 0.01180 -0.0589 0.5895 1.0000
5.250 0.8366 0.02275 0.01217 -0.0580 0.5682 1.0000
5.500 0.8623 0.02309 0.01259 -0.0573 0.5475 1.0000
5.750 0.8858 0.02353 0.01314 -0.0563 0.5265 1.0000
6.000 0.9109 0.02399 0.01366 -0.0555 0.5064 1.0000
6.250 0.9338 0.02455 0.01436 -0.0545 0.4862 1.0000
6.500 0.9559 0.02511 0.01504 -0.0532 0.4636 1.0000
6.750 0.9722 0.02566 0.01563 -0.0510 0.4352 1.0000
7.000 0.9851 0.02621 0.01617 -0.0483 0.4042 1.0000
7.250 0.9982 0.02682 0.01689 -0.0458 0.3767 1.0000
7.500 1.0120 0.02745 0.01770 -0.0434 0.3517 1.0000
7.750 1.0212 0.02810 0.01844 -0.0404 0.3199 1.0000
8.000 1.0237 0.02893 0.01917 -0.0366 0.2756 1.0000
8.250 1.0246 0.03014 0.02014 -0.0327 0.2292 1.0000
8.500 1.0258 0.03169 0.02156 -0.0292 0.1701 1.0000
8.750 1.0221 0.03395 0.02329 -0.0258 0.1121 1.0000
9.250 1.0193 0.03875 0.02772 -0.0203 0.0790 1.0000
9.500 1.0204 0.04101 0.03004 -0.0180 0.0705 1.0000
9.750 1.0187 0.04357 0.03261 -0.0157 0.0648 1.0000
10.000 1.0228 0.04584 0.03510 -0.0138 0.0597 1.0000
10.250 1.0248 0.04837 0.03768 -0.0121 0.0548 1.0000
10.500 1.0341 0.05078 0.04022 -0.0104 0.0508 1.0000
10.750 1.0498 0.05299 0.04273 -0.0089 0.0471 1.0000
11.000 1.0617 0.05547 0.04543 -0.0077 0.0433 1.0000
11.250 1.0816 0.05854 0.04856 -0.0069 0.0400 1.0000
11.500 1.0896 0.06160 0.05204 -0.0056 0.0389 1.0000
11.750 1.0910 0.06499 0.05581 -0.0045 0.0379 1.0000
12.000 1.0867 0.06863 0.05978 -0.0036 0.0370 1.0000
12.250 1.0784 0.07254 0.06400 -0.0031 0.0362 1.0000
12.500 1.0680 0.07678 0.06852 -0.0032 0.0357 1.0000
12.750 1.0549 0.08148 0.07348 -0.0039 0.0354 1.0000
13.000 1.0391 0.08675 0.07899 -0.0055 0.0350 1.0000
13.250 1.0215 0.09267 0.08513 -0.0079 0.0350 1.0000
13.500 1.0023 0.09939 0.09207 -0.0112 0.0355 1.0000
13.750 0.9818 0.10700 0.09985 -0.0156 0.0361 1.0000
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Polar data table (+)
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