GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 200,000 Max Cl/Cd: 79.84 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe419-il-200000.txt Download as CSV file: xf-goe419-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3698 0.09578 0.09237 -0.0232 1.0000 0.0249
-7.750 -0.3718 0.09398 0.09063 -0.0234 1.0000 0.0253
-7.500 -0.3743 0.09224 0.08896 -0.0240 1.0000 0.0256
-7.250 -0.3708 0.08995 0.08671 -0.0264 1.0000 0.0258
-7.000 -0.3653 0.08739 0.08419 -0.0285 1.0000 0.0260
-6.750 -0.3583 0.08476 0.08159 -0.0307 1.0000 0.0261
-6.500 -0.3517 0.08206 0.07891 -0.0319 1.0000 0.0262
-6.250 -0.3462 0.07940 0.07626 -0.0325 1.0000 0.0263
-6.000 -0.3415 0.07683 0.07369 -0.0327 1.0000 0.0263
-5.750 -0.3358 0.07416 0.07100 -0.0329 1.0000 0.0264
-5.500 -0.3282 0.07133 0.06815 -0.0332 1.0000 0.0264
-5.250 -0.3272 0.06574 0.06257 -0.0337 1.0000 0.0270
-5.000 -0.3257 0.06192 0.05878 -0.0324 1.0000 0.0277
-4.750 -0.3008 0.05770 0.05446 -0.0356 0.9969 0.0290
-4.500 -0.2655 0.05342 0.05008 -0.0412 0.9930 0.0309
-4.250 -0.2269 0.04909 0.04559 -0.0470 0.9883 0.0334
-4.000 -0.1684 0.04532 0.04139 -0.0549 0.9843 0.0389
-3.750 -0.1314 0.03950 0.03527 -0.0597 0.9802 0.0402
-3.500 -0.0930 0.03835 0.03380 -0.0624 0.9746 0.0521
-3.250 -0.0640 0.03281 0.02827 -0.0659 0.9714 0.0552
-3.000 -0.0231 0.03082 0.02568 -0.0683 0.9655 0.0660
-2.750 0.0090 0.02719 0.02207 -0.0708 0.9606 0.0706
-2.500 0.0551 0.02333 0.01761 -0.0734 0.9574 0.0612
-2.000 0.1336 0.01660 0.00954 -0.0753 0.9463 0.0468
-1.750 0.1712 0.01514 0.00769 -0.0765 0.9406 0.0517
-1.500 0.2089 0.01421 0.00664 -0.0783 0.9351 0.0654
-1.250 0.2498 0.01296 0.00541 -0.0809 0.9320 0.0759
-1.000 0.2839 0.01230 0.00474 -0.0821 0.9246 0.0887
-0.750 0.3242 0.01139 0.00399 -0.0845 0.9199 0.1257
-0.500 0.3842 0.00889 0.00370 -0.0917 0.9195 1.0000
-0.250 0.4213 0.00878 0.00342 -0.0934 0.9100 1.0000
0.000 0.4601 0.00867 0.00317 -0.0956 0.9008 1.0000
0.250 0.4976 0.00859 0.00299 -0.0974 0.8904 1.0000
0.500 0.5302 0.00859 0.00290 -0.0982 0.8777 1.0000
0.750 0.5586 0.00865 0.00289 -0.0981 0.8631 1.0000
1.000 0.5852 0.00873 0.00291 -0.0977 0.8477 1.0000
1.250 0.6110 0.00882 0.00296 -0.0970 0.8322 1.0000
1.500 0.6364 0.00891 0.00306 -0.0963 0.8164 1.0000
1.750 0.6616 0.00900 0.00313 -0.0955 0.8007 1.0000
2.000 0.6867 0.00909 0.00320 -0.0947 0.7849 1.0000
2.250 0.7079 0.00910 0.00316 -0.0928 0.7544 1.0000
2.500 0.7265 0.00910 0.00297 -0.0900 0.7017 1.0000
2.750 0.7459 0.00935 0.00295 -0.0877 0.6465 1.0000
3.000 0.7604 0.00990 0.00313 -0.0844 0.5550 1.0000
3.250 0.7627 0.01139 0.00341 -0.0794 0.3405 1.0000
3.500 0.7636 0.01411 0.00456 -0.0751 0.0400 1.0000
3.750 0.7853 0.01477 0.00538 -0.0736 0.0334 1.0000
4.000 0.8068 0.01544 0.00626 -0.0722 0.0321 1.0000
4.250 0.8267 0.01626 0.00724 -0.0705 0.0309 1.0000
4.500 0.8444 0.01727 0.00834 -0.0686 0.0264 1.0000
4.750 0.8610 0.01852 0.00965 -0.0663 0.0258 1.0000
5.000 0.8795 0.01989 0.01106 -0.0643 0.0266 1.0000
5.250 0.9016 0.02155 0.01284 -0.0627 0.0290 1.0000
5.500 0.9313 0.02430 0.01549 -0.0624 0.0337 1.0000
5.750 0.9667 0.02585 0.01720 -0.0619 0.0458 1.0000
6.000 1.0172 0.02755 0.01967 -0.0604 0.0861 1.0000
7.750 1.0599 0.04272 0.03696 -0.0436 0.0327 1.0000
8.000 1.0653 0.04195 0.03676 -0.0391 0.0292 1.0000
8.250 1.0651 0.04561 0.04074 -0.0361 0.0274 1.0000
8.500 1.0615 0.04949 0.04488 -0.0332 0.0262 1.0000
8.750 1.0546 0.05333 0.04894 -0.0303 0.0254 1.0000
9.000 1.0430 0.05704 0.05283 -0.0271 0.0248 1.0000
9.250 1.0259 0.06032 0.05627 -0.0235 0.0246 1.0000
9.500 1.0054 0.06385 0.05996 -0.0208 0.0245 1.0000
9.750 0.9821 0.06794 0.06422 -0.0193 0.0247 1.0000
10.000 0.9566 0.07285 0.06930 -0.0192 0.0251 1.0000
10.250 0.9301 0.07870 0.07531 -0.0207 0.0258 1.0000
10.500 0.9033 0.08556 0.08230 -0.0236 0.0266 1.0000
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Polar data table (+)
Polar graphs
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