GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 100,000 Max Cl/Cd: 44.06 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe599-il-100000-n5.txt Download as CSV file: xf-goe599-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5822 0.08815 0.08308 -0.0320 1.0000 0.0254
-10.000 -0.6428 0.06638 0.06122 -0.0496 1.0000 0.0233
-9.750 -0.6720 0.06066 0.05531 -0.0523 1.0000 0.0229
-9.500 -0.6898 0.05658 0.05102 -0.0518 1.0000 0.0229
-9.250 -0.7017 0.05259 0.04678 -0.0506 1.0000 0.0229
-9.000 -0.7087 0.04876 0.04267 -0.0490 1.0000 0.0230
-8.750 -0.7103 0.04522 0.03884 -0.0473 1.0000 0.0233
-8.500 -0.7068 0.04210 0.03544 -0.0456 1.0000 0.0238
-8.250 -0.6996 0.03934 0.03238 -0.0439 1.0000 0.0244
-8.000 -0.6888 0.03714 0.02993 -0.0424 1.0000 0.0255
-7.750 -0.6759 0.03509 0.02759 -0.0409 1.0000 0.0272
-7.500 -0.6618 0.03276 0.02485 -0.0393 1.0000 0.0289
-7.250 -0.6457 0.03043 0.02208 -0.0377 1.0000 0.0302
-7.000 -0.6273 0.02853 0.01977 -0.0362 1.0000 0.0315
-6.750 -0.6097 0.02660 0.01774 -0.0350 1.0000 0.0340
-6.500 -0.5903 0.02536 0.01639 -0.0339 1.0000 0.0372
-6.250 -0.5700 0.02400 0.01482 -0.0326 1.0000 0.0400
-6.000 -0.5499 0.02268 0.01338 -0.0315 1.0000 0.0437
-5.750 -0.5299 0.02165 0.01233 -0.0304 1.0000 0.0486
-5.500 -0.5089 0.02075 0.01127 -0.0293 1.0000 0.0535
-5.250 -0.4882 0.01988 0.01042 -0.0285 1.0000 0.0607
-5.000 -0.4665 0.01919 0.00963 -0.0276 1.0000 0.0683
-4.750 -0.4444 0.01863 0.00910 -0.0268 1.0000 0.0809
-4.500 -0.4219 0.01801 0.00848 -0.0261 1.0000 0.0989
-4.250 -0.3991 0.01736 0.00785 -0.0256 1.0000 0.1243
-4.000 -0.3761 0.01668 0.00742 -0.0253 1.0000 0.1676
-3.750 -0.3527 0.01620 0.00718 -0.0251 1.0000 0.2325
-3.500 -0.3212 0.01578 0.00695 -0.0264 0.9971 0.2978
-3.250 -0.2871 0.01530 0.00681 -0.0283 0.9930 0.3816
-3.000 -0.2538 0.01491 0.00674 -0.0298 0.9883 0.4668
-2.750 -0.2195 0.01471 0.00667 -0.0313 0.9836 0.5269
-2.500 -0.1860 0.01455 0.00659 -0.0326 0.9780 0.5796
-2.250 -0.1527 0.01441 0.00652 -0.0337 0.9727 0.6270
-2.000 -0.1204 0.01427 0.00648 -0.0346 0.9668 0.6742
-1.750 -0.0876 0.01415 0.00646 -0.0354 0.9614 0.7230
-1.500 -0.0577 0.01404 0.00647 -0.0354 0.9546 0.7751
-1.250 -0.0225 0.01397 0.00650 -0.0364 0.9503 0.8318
-1.000 0.0105 0.01394 0.00653 -0.0370 0.9429 0.8887
-0.750 0.0586 0.01394 0.00651 -0.0410 0.9389 0.9426
-0.500 0.1138 0.01389 0.00640 -0.0467 0.9357 0.9838
-0.250 0.1545 0.01378 0.00623 -0.0496 0.9252 1.0000
0.000 0.1884 0.01364 0.00603 -0.0509 0.9133 1.0000
0.250 0.2224 0.01350 0.00585 -0.0521 0.9022 1.0000
0.500 0.2569 0.01337 0.00569 -0.0534 0.8924 1.0000
0.750 0.2863 0.01332 0.00561 -0.0537 0.8806 1.0000
1.000 0.3164 0.01327 0.00556 -0.0541 0.8694 1.0000
1.250 0.3475 0.01322 0.00551 -0.0547 0.8587 1.0000
1.500 0.3792 0.01316 0.00547 -0.0553 0.8475 1.0000
1.750 0.4098 0.01306 0.00537 -0.0554 0.8304 1.0000
2.000 0.4413 0.01292 0.00521 -0.0555 0.8084 1.0000
2.250 0.4688 0.01289 0.00513 -0.0548 0.7810 1.0000
2.500 0.4947 0.01291 0.00512 -0.0540 0.7521 1.0000
2.750 0.5197 0.01296 0.00515 -0.0529 0.7195 1.0000
3.000 0.5439 0.01306 0.00519 -0.0518 0.6813 1.0000
3.250 0.5684 0.01321 0.00524 -0.0507 0.6387 1.0000
3.500 0.5921 0.01345 0.00533 -0.0494 0.5866 1.0000
3.750 0.6129 0.01391 0.00544 -0.0477 0.5107 1.0000
4.000 0.6311 0.01463 0.00569 -0.0458 0.4212 1.0000
4.250 0.6486 0.01552 0.00609 -0.0440 0.3259 1.0000
4.500 0.6611 0.01716 0.00676 -0.0419 0.1562 1.0000
4.750 0.6817 0.01805 0.00746 -0.0408 0.1158 1.0000
5.000 0.7037 0.01874 0.00810 -0.0398 0.1008 1.0000
5.250 0.7254 0.01943 0.00878 -0.0388 0.0934 1.0000
5.500 0.7472 0.02007 0.00953 -0.0378 0.0891 1.0000
5.750 0.7685 0.02075 0.01030 -0.0368 0.0849 1.0000
6.000 0.7882 0.02159 0.01115 -0.0355 0.0807 1.0000
6.250 0.8086 0.02239 0.01204 -0.0343 0.0776 1.0000
6.500 0.8291 0.02325 0.01301 -0.0331 0.0753 1.0000
6.750 0.8500 0.02421 0.01409 -0.0320 0.0728 1.0000
7.000 0.8712 0.02530 0.01520 -0.0310 0.0698 1.0000
7.250 0.8926 0.02661 0.01654 -0.0302 0.0651 1.0000
7.500 0.9142 0.02756 0.01768 -0.0294 0.0593 1.0000
7.750 0.9349 0.02910 0.01917 -0.0287 0.0538 1.0000
8.000 0.9562 0.03034 0.02073 -0.0277 0.0485 1.0000
8.250 0.9757 0.03157 0.02214 -0.0267 0.0433 1.0000
8.500 0.9947 0.03324 0.02399 -0.0256 0.0387 1.0000
8.750 1.0135 0.03496 0.02601 -0.0243 0.0347 1.0000
9.000 1.0297 0.03606 0.02713 -0.0232 0.0322 1.0000
9.250 1.0452 0.03845 0.03004 -0.0214 0.0288 1.0000
9.500 1.0586 0.04065 0.03256 -0.0197 0.0268 1.0000
9.750 1.0705 0.04244 0.03455 -0.0180 0.0255 1.0000
10.000 1.0810 0.04394 0.03613 -0.0164 0.0245 1.0000
10.250 1.0798 0.04809 0.04090 -0.0132 0.0233 1.0000
10.500 1.0732 0.05189 0.04519 -0.0100 0.0223 1.0000
10.750 1.0616 0.05528 0.04893 -0.0065 0.0217 1.0000
11.000 1.0470 0.05880 0.05276 -0.0035 0.0212 1.0000
11.250 1.0292 0.06277 0.05700 -0.0015 0.0210 1.0000
11.500 1.0083 0.06741 0.06190 -0.0007 0.0209 1.0000
11.750 0.9844 0.07298 0.06772 -0.0016 0.0210 1.0000
12.000 0.9574 0.07990 0.07484 -0.0046 0.0213 1.0000
12.250 0.9283 0.08858 0.08370 -0.0099 0.0218 1.0000
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Polar data table (+)
Polar graphs
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