SIKORSKY GS-1 AIRFOIL (gs1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY GS-1 AIRFOIL (gs1-il) Reynolds number: 200,000 Max Cl/Cd: 74.4 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gs1-il-200000-n5.txt Download as CSV file: xf-gs1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY GS-1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6863 0.05607 0.05134 -0.0828 1.0000 0.0419
-12.250 -0.7374 0.04732 0.04241 -0.0887 1.0000 0.0418
-12.000 -0.7814 0.04262 0.03758 -0.0896 1.0000 0.0416
-11.750 -0.8007 0.03962 0.03439 -0.0893 0.9971 0.0418
-11.500 -0.7845 0.03604 0.03045 -0.0940 0.9890 0.0424
-11.250 -0.7636 0.03336 0.02740 -0.0973 0.9829 0.0431
-11.000 -0.7412 0.03164 0.02555 -0.0989 0.9769 0.0437
-10.750 -0.7140 0.03035 0.02421 -0.1006 0.9721 0.0444
-10.500 -0.6849 0.02909 0.02286 -0.1026 0.9683 0.0452
-10.250 -0.6616 0.02787 0.02151 -0.1032 0.9615 0.0459
-10.000 -0.6323 0.02656 0.02005 -0.1049 0.9574 0.0468
-9.750 -0.6027 0.02533 0.01864 -0.1065 0.9535 0.0478
-9.500 -0.5784 0.02428 0.01740 -0.1067 0.9463 0.0487
-9.250 -0.5484 0.02322 0.01622 -0.1080 0.9418 0.0497
-9.000 -0.5201 0.02240 0.01538 -0.1088 0.9365 0.0508
-8.750 -0.4941 0.02169 0.01462 -0.1090 0.9292 0.0521
-8.500 -0.4631 0.02092 0.01374 -0.1101 0.9244 0.0537
-8.250 -0.4376 0.02023 0.01293 -0.1100 0.9167 0.0553
-8.000 -0.4097 0.01950 0.01213 -0.1103 0.9097 0.0568
-7.750 -0.3808 0.01885 0.01145 -0.1109 0.9035 0.0584
-7.500 -0.3551 0.01832 0.01085 -0.1106 0.8947 0.0604
-7.250 -0.3240 0.01775 0.01016 -0.1113 0.8888 0.0630
-7.000 -0.2999 0.01723 0.00963 -0.1108 0.8789 0.0654
-6.750 -0.2700 0.01675 0.00909 -0.1112 0.8720 0.0687
-6.500 -0.2444 0.01636 0.00860 -0.1107 0.8620 0.0720
-6.250 -0.2157 0.01588 0.00810 -0.1110 0.8543 0.0756
-6.000 -0.1900 0.01554 0.00770 -0.1105 0.8439 0.0799
-5.750 -0.1618 0.01517 0.00727 -0.1105 0.8353 0.0847
-5.500 -0.1355 0.01488 0.00694 -0.1101 0.8249 0.0904
-5.250 -0.1081 0.01458 0.00660 -0.1099 0.8155 0.0964
-5.000 -0.0812 0.01434 0.00630 -0.1096 0.8051 0.1036
-4.750 -0.0544 0.01409 0.00604 -0.1093 0.7949 0.1108
-4.500 -0.0268 0.01392 0.00577 -0.1091 0.7848 0.1192
-4.250 -0.0006 0.01371 0.00557 -0.1087 0.7741 0.1273
-4.000 0.0269 0.01355 0.00532 -0.1084 0.7641 0.1359
-3.750 0.0532 0.01337 0.00514 -0.1080 0.7531 0.1447
-3.500 0.0801 0.01322 0.00494 -0.1076 0.7428 0.1534
-3.250 0.1070 0.01309 0.00475 -0.1073 0.7323 0.1629
-3.000 0.1335 0.01294 0.00460 -0.1069 0.7217 0.1723
-2.750 0.1605 0.01283 0.00443 -0.1065 0.7119 0.1829
-2.500 0.1869 0.01271 0.00432 -0.1061 0.7012 0.1949
-2.250 0.2137 0.01261 0.00421 -0.1057 0.6918 0.2081
-2.000 0.2403 0.01253 0.00412 -0.1053 0.6818 0.2227
-1.750 0.2670 0.01246 0.00406 -0.1050 0.6725 0.2390
-1.500 0.2937 0.01241 0.00400 -0.1046 0.6632 0.2562
-1.250 0.3203 0.01237 0.00397 -0.1042 0.6543 0.2742
-1.000 0.3470 0.01235 0.00394 -0.1038 0.6454 0.2920
-0.750 0.3737 0.01233 0.00393 -0.1034 0.6370 0.3098
-0.500 0.4003 0.01233 0.00392 -0.1030 0.6285 0.3271
-0.250 0.4269 0.01234 0.00393 -0.1026 0.6203 0.3440
0.000 0.4534 0.01234 0.00394 -0.1022 0.6119 0.3616
0.250 0.4799 0.01236 0.00397 -0.1018 0.6043 0.3795
0.500 0.5061 0.01236 0.00401 -0.1013 0.5960 0.3975
0.750 0.5324 0.01238 0.00404 -0.1009 0.5887 0.4176
1.000 0.5584 0.01237 0.00411 -0.1004 0.5804 0.4394
1.250 0.5843 0.01239 0.00416 -0.0999 0.5728 0.4639
1.500 0.6099 0.01237 0.00425 -0.0993 0.5649 0.4937
1.750 0.6351 0.01234 0.00432 -0.0987 0.5572 0.5321
2.000 0.6593 0.01225 0.00443 -0.0978 0.5498 0.5922
2.250 0.6804 0.01195 0.00456 -0.0961 0.5421 0.7163
2.500 0.7316 0.01170 0.00468 -0.1003 0.5334 1.0000
2.750 0.7565 0.01184 0.00478 -0.0996 0.5254 1.0000
3.000 0.7814 0.01202 0.00487 -0.0989 0.5181 1.0000
3.250 0.8062 0.01217 0.00500 -0.0982 0.5098 1.0000
3.500 0.8309 0.01236 0.00510 -0.0975 0.5025 1.0000
3.750 0.8557 0.01252 0.00526 -0.0968 0.4945 1.0000
4.000 0.8802 0.01272 0.00540 -0.0961 0.4869 1.0000
4.250 0.9048 0.01291 0.00557 -0.0954 0.4794 1.0000
4.500 0.9291 0.01311 0.00574 -0.0946 0.4718 1.0000
4.750 0.9535 0.01332 0.00593 -0.0939 0.4648 1.0000
5.000 0.9777 0.01353 0.00613 -0.0932 0.4571 1.0000
5.250 1.0015 0.01377 0.00632 -0.0923 0.4501 1.0000
5.500 1.0256 0.01398 0.00658 -0.0916 0.4427 1.0000
5.750 1.0491 0.01424 0.00680 -0.0907 0.4358 1.0000
6.000 1.0726 0.01448 0.00706 -0.0899 0.4283 1.0000
6.250 1.0945 0.01474 0.00730 -0.0888 0.4187 1.0000
6.500 1.1160 0.01500 0.00756 -0.0876 0.4078 1.0000
6.750 1.1364 0.01530 0.00782 -0.0862 0.3967 1.0000
7.000 1.1565 0.01560 0.00811 -0.0848 0.3854 1.0000
7.250 1.1766 0.01590 0.00842 -0.0834 0.3741 1.0000
7.500 1.1954 0.01624 0.00873 -0.0819 0.3633 1.0000
7.750 1.2135 0.01659 0.00907 -0.0802 0.3517 1.0000
8.000 1.2309 0.01695 0.00944 -0.0784 0.3392 1.0000
8.250 1.2452 0.01735 0.00982 -0.0761 0.3258 1.0000
8.500 1.2579 0.01780 0.01024 -0.0735 0.3114 1.0000
8.750 1.2704 0.01830 0.01071 -0.0711 0.2980 1.0000
9.000 1.2822 0.01886 0.01125 -0.0686 0.2843 1.0000
9.250 1.2939 0.01946 0.01183 -0.0662 0.2698 1.0000
9.500 1.3043 0.02015 0.01248 -0.0637 0.2544 1.0000
9.750 1.3122 0.02098 0.01326 -0.0610 0.2364 1.0000
10.000 1.3192 0.02192 0.01415 -0.0584 0.2169 1.0000
10.250 1.3227 0.02310 0.01524 -0.0556 0.1939 1.0000
10.500 1.3228 0.02456 0.01657 -0.0526 0.1665 1.0000
10.750 1.3187 0.02641 0.01825 -0.0496 0.1376 1.0000
11.000 1.3151 0.02839 0.02010 -0.0470 0.1161 1.0000
11.250 1.3141 0.03032 0.02197 -0.0448 0.1025 1.0000
11.500 1.3144 0.03226 0.02390 -0.0430 0.0934 1.0000
11.750 1.3158 0.03422 0.02588 -0.0414 0.0870 1.0000
12.000 1.3177 0.03623 0.02793 -0.0400 0.0822 1.0000
12.250 1.3199 0.03829 0.03005 -0.0389 0.0781 1.0000
12.500 1.3194 0.04067 0.03248 -0.0378 0.0750 1.0000
12.750 1.3208 0.04300 0.03487 -0.0370 0.0722 1.0000
13.000 1.3231 0.04530 0.03726 -0.0363 0.0697 1.0000
13.250 1.3232 0.04792 0.03995 -0.0358 0.0673 1.0000
13.500 1.3219 0.05077 0.04285 -0.0354 0.0654 1.0000
13.750 1.3209 0.05367 0.04581 -0.0351 0.0636 1.0000
14.000 1.3230 0.05630 0.04854 -0.0349 0.0618 1.0000
14.250 1.3242 0.05910 0.05143 -0.0349 0.0601 1.0000
14.500 1.3242 0.06209 0.05449 -0.0349 0.0584 1.0000
14.750 1.3229 0.06531 0.05776 -0.0351 0.0570 1.0000
15.000 1.3211 0.06862 0.06111 -0.0354 0.0557 1.0000
15.250 1.3241 0.07143 0.06403 -0.0356 0.0543 1.0000
15.500 1.3262 0.07437 0.06706 -0.0360 0.0529 1.0000
15.750 1.3278 0.07742 0.07019 -0.0364 0.0516 1.0000
16.000 1.3285 0.08063 0.07347 -0.0370 0.0503 1.0000
16.250 1.3285 0.08397 0.07683 -0.0376 0.0492 1.0000
16.500 1.3299 0.08710 0.08002 -0.0382 0.0482 1.0000
16.750 1.3330 0.09009 0.08312 -0.0388 0.0469 1.0000
17.000 1.3356 0.09318 0.08631 -0.0395 0.0457 1.0000
17.250 1.3377 0.09635 0.08956 -0.0403 0.0446 1.0000
17.500 1.3392 0.09965 0.09292 -0.0413 0.0435 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY GS-1 AIRFOIL (gs1-il)