GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.62 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe55-il-1000000-n5.txt Download as CSV file: xf-goe55-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -1.0591 0.02837 0.02545 -0.0299 1.0000 0.0174
-11.000 -1.0338 0.02770 0.02474 -0.0299 1.0000 0.0177
-10.750 -1.0069 0.02789 0.02497 -0.0295 1.0000 0.0179
-10.500 -0.9806 0.02767 0.02474 -0.0293 1.0000 0.0181
-10.250 -0.9553 0.02685 0.02385 -0.0294 1.0000 0.0184
-10.000 -0.9297 0.02604 0.02296 -0.0294 1.0000 0.0186
-9.750 -0.9040 0.02515 0.02199 -0.0295 1.0000 0.0190
-9.500 -0.8787 0.02385 0.02053 -0.0298 1.0000 0.0194
-9.250 -0.8537 0.02212 0.01858 -0.0302 1.0000 0.0198
-9.000 -0.8280 0.02060 0.01683 -0.0306 1.0000 0.0203
-8.750 -0.8014 0.01959 0.01565 -0.0307 1.0000 0.0206
-8.500 -0.7745 0.01873 0.01465 -0.0308 1.0000 0.0209
-8.250 -0.7473 0.01797 0.01375 -0.0308 1.0000 0.0210
-8.000 -0.7205 0.01662 0.01221 -0.0311 1.0000 0.0215
-7.750 -0.6930 0.01606 0.01158 -0.0312 1.0000 0.0218
-7.500 -0.6652 0.01555 0.01102 -0.0311 1.0000 0.0221
-7.250 -0.6374 0.01505 0.01045 -0.0311 1.0000 0.0223
-7.000 -0.6094 0.01454 0.00988 -0.0311 1.0000 0.0226
-6.750 -0.5814 0.01415 0.00943 -0.0311 1.0000 0.0229
-6.500 -0.5532 0.01370 0.00893 -0.0311 1.0000 0.0232
-6.250 -0.5250 0.01315 0.00830 -0.0311 1.0000 0.0235
-6.000 -0.4967 0.01261 0.00767 -0.0311 1.0000 0.0238
-5.750 -0.4682 0.01211 0.00710 -0.0311 1.0000 0.0241
-5.500 -0.4398 0.01164 0.00657 -0.0310 1.0000 0.0244
-5.250 -0.4112 0.01122 0.00609 -0.0310 1.0000 0.0247
-5.000 -0.3826 0.01083 0.00565 -0.0310 1.0000 0.0250
-4.750 -0.3610 0.01123 0.00541 -0.0291 0.7577 0.0252
-4.500 -0.3331 0.01138 0.00513 -0.0290 0.6377 0.0255
-4.250 -0.3045 0.01162 0.00483 -0.0292 0.4719 0.0257
-4.000 -0.2758 0.01128 0.00428 -0.0293 0.4205 0.0261
-3.750 -0.2470 0.01100 0.00387 -0.0294 0.3910 0.0265
-3.500 -0.2183 0.01079 0.00357 -0.0294 0.3721 0.0269
-3.250 -0.1895 0.01061 0.00333 -0.0293 0.3584 0.0273
-3.000 -0.1608 0.01046 0.00312 -0.0293 0.3477 0.0277
-2.500 -0.1032 0.01018 0.00277 -0.0292 0.3331 0.0286
-2.250 -0.0744 0.01006 0.00261 -0.0292 0.3276 0.0291
-1.750 -0.0168 0.00984 0.00233 -0.0290 0.3188 0.0302
-1.500 0.0120 0.00975 0.00223 -0.0290 0.3151 0.0308
-1.250 0.0408 0.00969 0.00214 -0.0289 0.3099 0.0312
-1.000 0.0697 0.00959 0.00201 -0.0289 0.3048 0.0323
-0.750 0.0986 0.00950 0.00192 -0.0288 0.3015 0.0336
-0.500 0.1274 0.00944 0.00186 -0.0287 0.2968 0.0349
-0.250 0.1562 0.00941 0.00181 -0.0287 0.2890 0.0364
0.000 0.1849 0.00937 0.00176 -0.0286 0.2812 0.0381
0.250 0.2137 0.00934 0.00172 -0.0286 0.2752 0.0424
0.500 0.2425 0.00930 0.00170 -0.0285 0.2699 0.0483
0.750 0.2713 0.00927 0.00168 -0.0285 0.2604 0.0621
1.000 0.3001 0.00922 0.00172 -0.0285 0.2531 0.0875
1.250 0.3288 0.00925 0.00172 -0.0284 0.2437 0.0961
1.500 0.3575 0.00927 0.00174 -0.0284 0.2318 0.1034
1.750 0.3861 0.00936 0.00176 -0.0283 0.2100 0.1096
2.000 0.4145 0.00966 0.00187 -0.0284 0.1573 0.1186
2.250 0.4434 0.00970 0.00204 -0.0287 0.1271 0.2265
2.750 0.4948 0.00813 0.00227 -0.0280 0.0967 1.0000
3.000 0.5233 0.00842 0.00243 -0.0280 0.0736 1.0000
3.250 0.5517 0.00889 0.00270 -0.0281 0.0360 1.0000
3.500 0.5802 0.00907 0.00284 -0.0280 0.0338 1.0000
3.750 0.6087 0.00926 0.00301 -0.0279 0.0322 1.0000
4.000 0.6371 0.00946 0.00319 -0.0278 0.0309 1.0000
4.250 0.6655 0.00966 0.00339 -0.0278 0.0299 1.0000
4.500 0.6938 0.00989 0.00362 -0.0277 0.0292 1.0000
4.750 0.7221 0.01009 0.00382 -0.0276 0.0289 1.0000
5.000 0.7503 0.01030 0.00403 -0.0275 0.0286 1.0000
5.250 0.7784 0.01052 0.00427 -0.0275 0.0282 1.0000
5.500 0.8065 0.01076 0.00452 -0.0274 0.0277 1.0000
5.750 0.8345 0.01102 0.00478 -0.0273 0.0273 1.0000
6.000 0.8625 0.01129 0.00508 -0.0272 0.0269 1.0000
6.250 0.8903 0.01158 0.00538 -0.0271 0.0265 1.0000
6.500 0.9181 0.01188 0.00571 -0.0270 0.0262 1.0000
6.750 0.9457 0.01220 0.00606 -0.0270 0.0258 1.0000
7.000 0.9733 0.01254 0.00643 -0.0269 0.0255 1.0000
7.250 1.0007 0.01291 0.00682 -0.0268 0.0251 1.0000
7.500 1.0279 0.01331 0.00726 -0.0267 0.0248 1.0000
7.750 1.0549 0.01374 0.00774 -0.0265 0.0244 1.0000
8.000 1.0816 0.01429 0.00833 -0.0264 0.0239 1.0000
8.250 1.1077 0.01499 0.00910 -0.0263 0.0234 1.0000
8.500 1.1340 0.01554 0.00972 -0.0261 0.0232 1.0000
8.750 1.1605 0.01595 0.01017 -0.0260 0.0230 1.0000
9.000 1.1870 0.01631 0.01058 -0.0258 0.0228 1.0000
9.250 1.2133 0.01672 0.01103 -0.0256 0.0226 1.0000
9.500 1.2393 0.01717 0.01154 -0.0254 0.0223 1.0000
9.750 1.2653 0.01760 0.01203 -0.0252 0.0219 1.0000
10.000 1.2910 0.01806 0.01254 -0.0250 0.0215 1.0000
10.250 1.3165 0.01851 0.01304 -0.0248 0.0210 1.0000
10.500 1.3419 0.01897 0.01356 -0.0245 0.0206 1.0000
10.750 1.3671 0.01944 0.01407 -0.0243 0.0202 1.0000
11.000 1.3923 0.01985 0.01451 -0.0241 0.0198 1.0000
11.250 1.4171 0.02033 0.01503 -0.0238 0.0194 1.0000
11.500 1.4410 0.02098 0.01572 -0.0235 0.0190 1.0000
11.750 1.4635 0.02185 0.01667 -0.0231 0.0185 1.0000
12.000 1.4879 0.02229 0.01719 -0.0228 0.0183 1.0000
12.250 1.5117 0.02281 0.01777 -0.0225 0.0179 1.0000
12.500 1.5349 0.02339 0.01843 -0.0221 0.0175 1.0000
12.750 1.5578 0.02400 0.01911 -0.0217 0.0170 1.0000
13.000 1.5805 0.02458 0.01976 -0.0213 0.0166 1.0000
13.250 1.6033 0.02511 0.02033 -0.0209 0.0160 1.0000
13.500 1.6260 0.02562 0.02088 -0.0205 0.0155 1.0000
13.750 1.6479 0.02623 0.02151 -0.0200 0.0149 1.0000
14.000 1.6675 0.02711 0.02248 -0.0194 0.0145 1.0000
14.250 1.6862 0.02806 0.02353 -0.0188 0.0140 1.0000
14.500 1.7042 0.02902 0.02458 -0.0181 0.0135 1.0000
14.750 1.7215 0.03000 0.02563 -0.0174 0.0129 1.0000
15.000 1.7376 0.03105 0.02673 -0.0166 0.0123 1.0000
15.250 1.7512 0.03232 0.02807 -0.0158 0.0117 1.0000
15.500 1.7600 0.03396 0.02983 -0.0147 0.0114 1.0000
15.750 1.7631 0.03589 0.03190 -0.0133 0.0110 1.0000
16.000 1.7537 0.03863 0.03478 -0.0116 0.0108 1.0000
16.250 1.7322 0.04577 0.04216 -0.0171 0.0107 1.0000
16.500 1.6887 0.06110 0.05781 -0.0304 0.0110 1.0000
16.750 1.6272 0.07509 0.07198 -0.0384 0.0114 1.0000
17.000 1.5735 0.08731 0.08435 -0.0449 0.0116 1.0000
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