GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.7 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe55-il-1000000.txt Download as CSV file: xf-goe55-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 55 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5534 0.10363 0.10207 0.0281 1.0000 0.0211
-9.250 -0.5546 0.09885 0.09729 0.0266 1.0000 0.0212
-8.750 -0.6718 0.10125 0.09962 0.0369 1.0000 0.0211
-8.500 -0.6714 0.09659 0.09498 0.0342 1.0000 0.0212
-8.250 -0.6710 0.09161 0.09000 0.0306 1.0000 0.0212
-8.000 -0.6703 0.08552 0.08392 0.0257 1.0000 0.0216
-7.750 -0.6576 0.08267 0.08107 0.0233 1.0000 0.0218
-7.500 -0.6435 0.07968 0.07808 0.0206 1.0000 0.0221
-7.250 -0.6280 0.07622 0.07461 0.0169 1.0000 0.0225
-7.000 -0.6108 0.07213 0.07049 0.0122 1.0000 0.0232
-6.750 -0.5804 0.05961 0.05778 -0.0037 1.0000 0.0255
-6.250 -0.5415 0.01964 0.01566 -0.0258 1.0000 0.0261
-6.000 -0.5141 0.01883 0.01480 -0.0260 1.0000 0.0266
-5.750 -0.4865 0.01850 0.01446 -0.0260 1.0000 0.0270
-5.500 -0.4585 0.01772 0.01361 -0.0261 1.0000 0.0275
-5.250 -0.4301 0.01609 0.01174 -0.0264 1.0000 0.0279
-5.000 -0.4014 0.01486 0.01033 -0.0266 1.0000 0.0283
-4.750 -0.3727 0.01386 0.00918 -0.0267 1.0000 0.0289
-4.500 -0.3439 0.01307 0.00827 -0.0268 1.0000 0.0294
-4.250 -0.3152 0.01257 0.00769 -0.0267 1.0000 0.0300
-4.000 -0.2864 0.01199 0.00703 -0.0267 1.0000 0.0303
-3.750 -0.2576 0.01156 0.00654 -0.0267 1.0000 0.0306
-3.500 -0.2287 0.01081 0.00571 -0.0267 1.0000 0.0309
-3.250 -0.1983 0.00983 0.00463 -0.0271 0.9374 0.0316
-3.000 -0.1788 0.01036 0.00425 -0.0248 0.6664 0.0321
-2.750 -0.1503 0.01059 0.00390 -0.0250 0.4850 0.0328
-2.500 -0.1215 0.01057 0.00364 -0.0251 0.4170 0.0335
-2.250 -0.0928 0.01047 0.00343 -0.0251 0.3884 0.0345
-2.000 -0.0639 0.01031 0.00319 -0.0251 0.3721 0.0352
-1.750 -0.0350 0.01015 0.00297 -0.0251 0.3613 0.0359
-1.500 -0.0061 0.01002 0.00279 -0.0250 0.3524 0.0365
-1.250 0.0228 0.00989 0.00263 -0.0250 0.3463 0.0370
-1.000 0.0520 0.00961 0.00229 -0.0251 0.3392 0.0390
-0.750 0.0809 0.00951 0.00218 -0.0250 0.3328 0.0408
-0.500 0.1098 0.00943 0.00209 -0.0250 0.3274 0.0429
-0.250 0.1386 0.00940 0.00202 -0.0249 0.3213 0.0450
0.000 0.1676 0.00927 0.00191 -0.0249 0.3167 0.0511
0.250 0.1966 0.00917 0.00185 -0.0248 0.3113 0.0643
0.500 0.2254 0.00913 0.00188 -0.0249 0.3039 0.0956
0.750 0.2542 0.00907 0.00187 -0.0248 0.2999 0.1078
1.000 0.2829 0.00904 0.00185 -0.0247 0.2943 0.1196
1.250 0.3119 0.00893 0.00187 -0.0248 0.2880 0.1744
1.500 0.3414 0.00832 0.00193 -0.0254 0.2826 0.4226
1.750 0.3633 0.00676 0.00187 -0.0240 0.2765 1.0000
2.000 0.3920 0.00683 0.00190 -0.0239 0.2701 1.0000
2.250 0.4208 0.00691 0.00193 -0.0238 0.2620 1.0000
2.500 0.4495 0.00699 0.00197 -0.0237 0.2528 1.0000
2.750 0.4781 0.00710 0.00201 -0.0236 0.2387 1.0000
3.000 0.5066 0.00735 0.00207 -0.0236 0.1996 1.0000
3.250 0.5349 0.00781 0.00227 -0.0237 0.1473 1.0000
3.500 0.5633 0.00814 0.00245 -0.0238 0.1213 1.0000
3.750 0.5916 0.00851 0.00266 -0.0238 0.0921 1.0000
4.000 0.6198 0.00917 0.00303 -0.0239 0.0418 1.0000
4.250 0.6482 0.00945 0.00328 -0.0239 0.0374 1.0000
4.500 0.6766 0.00966 0.00351 -0.0238 0.0364 1.0000
4.750 0.7050 0.00991 0.00377 -0.0237 0.0354 1.0000
5.000 0.7332 0.01018 0.00405 -0.0236 0.0342 1.0000
5.250 0.7614 0.01049 0.00437 -0.0236 0.0331 1.0000
5.500 0.7895 0.01086 0.00476 -0.0235 0.0320 1.0000
5.750 0.8174 0.01135 0.00531 -0.0234 0.0310 1.0000
6.000 0.8452 0.01181 0.00581 -0.0234 0.0305 1.0000
6.250 0.8730 0.01215 0.00619 -0.0233 0.0302 1.0000
6.500 0.9006 0.01254 0.00661 -0.0232 0.0299 1.0000
6.750 0.9282 0.01293 0.00703 -0.0231 0.0294 1.0000
7.000 0.9555 0.01335 0.00749 -0.0230 0.0288 1.0000
7.250 0.9827 0.01382 0.00801 -0.0228 0.0284 1.0000
7.500 1.0096 0.01432 0.00855 -0.0227 0.0279 1.0000
7.750 1.0364 0.01485 0.00912 -0.0226 0.0274 1.0000
8.000 1.0628 0.01543 0.00974 -0.0224 0.0269 1.0000
8.250 1.0890 0.01605 0.01039 -0.0223 0.0263 1.0000
8.500 1.1139 0.01701 0.01139 -0.0221 0.0256 1.0000
8.750 1.1359 0.01893 0.01342 -0.0216 0.0248 1.0000
9.000 1.1621 0.01931 0.01386 -0.0214 0.0246 1.0000
9.250 1.1880 0.01976 0.01437 -0.0212 0.0243 1.0000
9.500 1.2136 0.02022 0.01490 -0.0209 0.0238 1.0000
9.750 1.2384 0.02087 0.01563 -0.0206 0.0233 1.0000
10.000 1.2628 0.02160 0.01643 -0.0203 0.0229 1.0000
10.250 1.2869 0.02231 0.01721 -0.0200 0.0224 1.0000
10.500 1.3110 0.02293 0.01788 -0.0197 0.0219 1.0000
10.750 1.3349 0.02352 0.01852 -0.0194 0.0214 1.0000
11.000 1.3574 0.02436 0.01940 -0.0190 0.0209 1.0000
11.250 1.3738 0.02653 0.02167 -0.0183 0.0203 1.0000
11.500 1.3928 0.02799 0.02328 -0.0177 0.0199 1.0000
11.750 1.4153 0.02854 0.02394 -0.0173 0.0197 1.0000
12.000 1.4369 0.02920 0.02470 -0.0168 0.0193 1.0000
12.250 1.4575 0.03000 0.02560 -0.0163 0.0188 1.0000
12.500 1.4770 0.03088 0.02658 -0.0158 0.0184 1.0000
12.750 1.4955 0.03184 0.02764 -0.0152 0.0180 1.0000
13.000 1.5135 0.03277 0.02864 -0.0147 0.0176 1.0000
13.250 1.5309 0.03368 0.02963 -0.0141 0.0173 1.0000
13.500 1.5469 0.03470 0.03070 -0.0135 0.0171 1.0000
13.750 1.5594 0.03603 0.03209 -0.0128 0.0168 1.0000
14.000 1.5602 0.03841 0.03459 -0.0116 0.0165 1.0000
14.500 1.5203 0.05011 0.04673 -0.0173 0.0162 1.0000
14.750 1.5152 0.05683 0.05363 -0.0240 0.0161 1.0000
15.000 1.5010 0.06434 0.06129 -0.0296 0.0161 1.0000
15.250 1.4813 0.07200 0.06908 -0.0345 0.0160 1.0000
15.500 1.4570 0.08004 0.07724 -0.0392 0.0160 1.0000
15.750 1.4315 0.08815 0.08548 -0.0436 0.0160 1.0000
16.000 1.4056 0.09643 0.09387 -0.0481 0.0160 1.0000
16.250 1.3778 0.10519 0.10274 -0.0528 0.0160 1.0000
16.500 1.3532 0.11421 0.11189 -0.0579 0.0159 1.0000
16.750 1.3247 0.12444 0.12225 -0.0636 0.0159 1.0000
17.000 1.2916 0.13634 0.13430 -0.0704 0.0159 1.0000
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