GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 200,000 Max Cl/Cd: 74.73 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe177-il-200000.txt Download as CSV file: xf-goe177-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3199 0.09041 0.08723 -0.0188 1.0000 0.0332
-7.000 -0.3178 0.08783 0.08471 -0.0196 1.0000 0.0346
-6.750 -0.3135 0.08519 0.08213 -0.0223 1.0000 0.0367
-6.500 -0.3059 0.08310 0.08009 -0.0296 1.0000 0.0381
-6.250 -0.2937 0.08039 0.07739 -0.0353 1.0000 0.0385
-6.000 -0.2939 0.07533 0.07240 -0.0349 1.0000 0.0392
-5.750 -0.2935 0.07256 0.06969 -0.0306 1.0000 0.0402
-5.500 -0.2887 0.07012 0.06729 -0.0294 1.0000 0.0413
-5.250 -0.2833 0.06770 0.06490 -0.0293 1.0000 0.0426
-5.000 -0.2663 0.06449 0.06168 -0.0324 0.9984 0.0447
-4.750 -0.1813 0.05679 0.05358 -0.0556 0.9909 0.0503
-4.500 -0.1575 0.05161 0.04847 -0.0576 0.9851 0.0521
-4.250 -0.1174 0.04783 0.04461 -0.0630 0.9779 0.0554
-4.000 -0.0497 0.04065 0.03689 -0.0764 0.9713 0.0632
-3.750 -0.0142 0.03690 0.03315 -0.0799 0.9634 0.0653
-3.500 0.0429 0.03428 0.02980 -0.0863 0.9557 0.0757
-3.250 0.0839 0.02003 0.01430 -0.0902 0.9466 0.0384
-3.000 0.1212 0.01633 0.00992 -0.0920 0.9334 0.0398
-2.750 0.1555 0.01543 0.00886 -0.0928 0.9150 0.0459
-2.500 0.1871 0.01406 0.00718 -0.0928 0.8924 0.0524
-2.250 0.2174 0.01347 0.00640 -0.0925 0.8667 0.0637
-2.000 0.2453 0.01303 0.00585 -0.0919 0.8388 0.0816
-1.750 0.2722 0.01275 0.00533 -0.0911 0.8112 0.1038
-1.500 0.2981 0.01236 0.00480 -0.0904 0.7852 0.1208
-1.250 0.3244 0.01225 0.00448 -0.0898 0.7609 0.1321
-1.000 0.3507 0.01206 0.00422 -0.0892 0.7384 0.1438
-0.750 0.3770 0.01190 0.00396 -0.0887 0.7179 0.1538
-0.500 0.4037 0.01177 0.00370 -0.0883 0.6978 0.1615
-0.250 0.4305 0.01165 0.00352 -0.0879 0.6787 0.1732
0.000 0.4572 0.01150 0.00339 -0.0875 0.6611 0.1948
0.250 0.4836 0.01102 0.00338 -0.0873 0.6437 0.3438
0.500 0.5063 0.00957 0.00324 -0.0857 0.6269 1.0000
0.750 0.5333 0.00975 0.00320 -0.0853 0.6097 1.0000
1.000 0.5601 0.00994 0.00319 -0.0850 0.5932 1.0000
1.250 0.5869 0.01014 0.00320 -0.0846 0.5773 1.0000
1.500 0.6135 0.01034 0.00323 -0.0843 0.5601 1.0000
1.750 0.6400 0.01051 0.00326 -0.0839 0.5400 1.0000
2.000 0.6661 0.01071 0.00327 -0.0835 0.5197 1.0000
2.250 0.6924 0.01089 0.00333 -0.0831 0.4993 1.0000
2.500 0.7188 0.01109 0.00341 -0.0828 0.4812 1.0000
2.750 0.7452 0.01129 0.00350 -0.0825 0.4651 1.0000
3.000 0.7718 0.01150 0.00363 -0.0823 0.4513 1.0000
3.250 0.7984 0.01172 0.00378 -0.0821 0.4387 1.0000
3.500 0.8250 0.01193 0.00398 -0.0818 0.4269 1.0000
3.750 0.8515 0.01216 0.00416 -0.0816 0.4159 1.0000
4.000 0.8778 0.01241 0.00435 -0.0814 0.4060 1.0000
4.250 0.9045 0.01262 0.00458 -0.0812 0.3959 1.0000
4.500 0.9307 0.01284 0.00482 -0.0809 0.3836 1.0000
4.750 0.9560 0.01308 0.00498 -0.0806 0.3653 1.0000
5.000 0.9817 0.01332 0.00520 -0.0803 0.3506 1.0000
5.250 1.0072 0.01356 0.00541 -0.0799 0.3293 1.0000
5.500 1.0328 0.01382 0.00567 -0.0796 0.3147 1.0000
5.750 1.0575 0.01416 0.00594 -0.0793 0.2876 1.0000
6.000 1.0808 0.01468 0.00622 -0.0788 0.2405 1.0000
6.250 1.0966 0.01635 0.00712 -0.0776 0.1235 1.0000
6.500 1.1190 0.01714 0.00782 -0.0770 0.0982 1.0000
6.750 1.1405 0.01802 0.00859 -0.0762 0.0614 1.0000
7.000 1.1620 0.01887 0.00952 -0.0753 0.0504 1.0000
7.250 1.1853 0.01946 0.01023 -0.0746 0.0379 1.0000
7.500 1.2070 0.02020 0.01096 -0.0737 0.0257 1.0000
7.750 1.2281 0.02101 0.01184 -0.0727 0.0228 1.0000
8.000 1.2481 0.02192 0.01290 -0.0715 0.0219 1.0000
8.250 1.2665 0.02296 0.01416 -0.0701 0.0216 1.0000
8.500 1.2822 0.02420 0.01566 -0.0684 0.0212 1.0000
8.750 1.2943 0.02567 0.01733 -0.0664 0.0202 1.0000
9.000 1.3029 0.02732 0.01914 -0.0641 0.0193 1.0000
9.250 1.3093 0.02903 0.02100 -0.0615 0.0192 1.0000
9.500 1.3118 0.03079 0.02289 -0.0584 0.0192 1.0000
9.750 1.3134 0.03270 0.02492 -0.0554 0.0193 1.0000
10.000 1.3160 0.03477 0.02710 -0.0527 0.0195 1.0000
10.250 1.3214 0.03696 0.02939 -0.0503 0.0199 1.0000
10.500 1.3316 0.03928 0.03183 -0.0481 0.0206 1.0000
10.750 1.3520 0.04207 0.03471 -0.0465 0.0216 1.0000
11.000 1.3842 0.04505 0.03782 -0.0462 0.0229 1.0000
11.250 1.2717 0.03955 0.03281 -0.0324 0.0224 1.0000
12.000 1.2978 0.05355 0.04816 -0.0259 0.0325 1.0000
12.250 1.2734 0.05913 0.05411 -0.0236 0.0348 1.0000
12.500 1.2502 0.06543 0.06091 -0.0217 0.0424 1.0000
12.750 1.2213 0.07062 0.06634 -0.0213 0.0430 1.0000
13.000 1.1940 0.07601 0.07193 -0.0217 0.0431 1.0000
13.250 1.1692 0.08131 0.07735 -0.0225 0.0428 1.0000
13.500 1.1444 0.08670 0.08287 -0.0238 0.0424 1.0000
13.750 1.1203 0.09195 0.08825 -0.0253 0.0419 1.0000
14.000 1.0965 0.09709 0.09350 -0.0270 0.0414 1.0000
14.250 1.0713 0.10157 0.09808 -0.0283 0.0410 1.0000
14.500 1.0465 0.10619 0.10280 -0.0301 0.0407 1.0000
14.750 1.0227 0.11138 0.10809 -0.0326 0.0404 1.0000
15.000 0.9997 0.11694 0.11374 -0.0356 0.0402 1.0000
15.250 0.9761 0.12299 0.11986 -0.0389 0.0397 1.0000
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Polar data table (+)
Polar graphs
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