GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 500,000 Max Cl/Cd: 88.12 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe54-il-500000-n5.txt Download as CSV file: xf-goe54-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5769 0.11907 0.11687 0.0461 1.0000 0.0122
-9.250 -0.5720 0.11533 0.11314 0.0445 1.0000 0.0123
-9.000 -0.5680 0.11124 0.10906 0.0425 1.0000 0.0124
-8.750 -0.5615 0.10823 0.10607 0.0412 1.0000 0.0127
-8.500 -0.5550 0.10512 0.10298 0.0398 1.0000 0.0129
-8.250 -0.5489 0.10185 0.09972 0.0381 1.0000 0.0131
-8.000 -0.5427 0.09862 0.09652 0.0363 1.0000 0.0133
-7.750 -0.5361 0.09544 0.09336 0.0344 1.0000 0.0140
-7.250 -0.5163 0.08822 0.08617 0.0276 1.0000 0.0157
-7.000 -0.5025 0.08451 0.08246 0.0236 1.0000 0.0160
-6.750 -0.4842 0.08019 0.07814 0.0178 1.0000 0.0175
-6.500 -0.4685 0.07657 0.07377 0.0137 0.7071 0.0175
-6.250 -0.4499 0.07255 0.06948 0.0092 0.6369 0.0175
-6.000 -0.4168 0.06581 0.06241 -0.0013 0.5811 0.0178
-5.750 -0.4028 0.06354 0.05995 -0.0014 0.5245 0.0181
-5.500 -0.3815 0.06071 0.05695 -0.0038 0.4940 0.0185
-5.250 -0.3571 0.05762 0.05371 -0.0067 0.4753 0.0192
-5.000 -0.3235 0.05352 0.04941 -0.0114 0.4636 0.0208
-4.750 -0.2876 0.04899 0.04458 -0.0157 0.4547 0.0210
-4.500 -0.2566 0.04513 0.04045 -0.0182 0.4461 0.0210
-4.250 -0.2341 0.04203 0.03727 -0.0194 0.4374 0.0212
-4.000 -0.2108 0.03981 0.03497 -0.0204 0.4283 0.0215
-3.750 -0.1848 0.03774 0.03278 -0.0214 0.4201 0.0219
-3.500 -0.1569 0.03568 0.03057 -0.0224 0.4122 0.0226
-3.250 -0.1199 0.03381 0.02831 -0.0228 0.4059 0.0247
-3.000 -0.0896 0.03162 0.02587 -0.0233 0.3992 0.0248
-2.750 -0.0601 0.02965 0.02364 -0.0237 0.3922 0.0248
-2.500 -0.0310 0.02786 0.02164 -0.0239 0.3855 0.0249
-2.250 -0.0045 0.02524 0.01894 -0.0249 0.3777 0.0252
-2.000 0.0225 0.02389 0.01751 -0.0254 0.3699 0.0257
-1.750 0.0507 0.02276 0.01625 -0.0257 0.3607 0.0264
-1.500 0.0799 0.02161 0.01493 -0.0258 0.3513 0.0273
-1.250 0.1116 0.02145 0.01443 -0.0250 0.3409 0.0294
-1.000 0.1412 0.02054 0.01327 -0.0249 0.3283 0.0295
-0.750 0.1702 0.01963 0.01214 -0.0249 0.3117 0.0295
-0.500 0.1992 0.01888 0.01117 -0.0249 0.2925 0.0296
-0.250 0.2280 0.01712 0.00925 -0.0253 0.2761 0.0301
0.250 0.2852 0.01549 0.00742 -0.0254 0.2569 0.0280
0.500 0.3142 0.01485 0.00663 -0.0252 0.2498 0.0274
0.750 0.3431 0.01430 0.00598 -0.0251 0.2446 0.0273
1.000 0.3717 0.01386 0.00544 -0.0249 0.2388 0.0275
1.250 0.4003 0.01351 0.00500 -0.0248 0.2337 0.0277
1.500 0.4287 0.01323 0.00467 -0.0246 0.2296 0.0284
1.750 0.4572 0.01302 0.00440 -0.0244 0.2252 0.0290
2.000 0.4855 0.01272 0.00408 -0.0243 0.2208 0.0289
2.250 0.5138 0.01249 0.00382 -0.0242 0.2170 0.0290
2.500 0.5421 0.01231 0.00363 -0.0240 0.2141 0.0292
2.750 0.5705 0.01218 0.00351 -0.0239 0.2118 0.0295
3.000 0.5990 0.01194 0.00330 -0.0239 0.2091 0.0301
3.250 0.6273 0.01185 0.00324 -0.0239 0.2061 0.0307
3.500 0.6556 0.01185 0.00325 -0.0239 0.2030 0.0319
3.750 0.6838 0.01189 0.00329 -0.0238 0.1998 0.0334
4.000 0.7121 0.01189 0.00331 -0.0237 0.1973 0.0339
4.250 0.7405 0.01188 0.00334 -0.0237 0.1946 0.0346
4.500 0.7686 0.01192 0.00341 -0.0236 0.1912 0.0353
4.750 0.7968 0.01196 0.00345 -0.0235 0.1876 0.0368
5.000 0.8248 0.01209 0.00357 -0.0235 0.1838 0.0392
5.250 0.8528 0.01218 0.00370 -0.0234 0.1807 0.0418
5.500 0.8807 0.01227 0.00381 -0.0233 0.1764 0.0449
5.750 0.9086 0.01241 0.00395 -0.0231 0.1717 0.0505
6.000 0.9322 0.01092 0.00422 -0.0226 0.1664 1.0000
6.250 0.9598 0.01113 0.00437 -0.0225 0.1574 1.0000
6.500 0.9873 0.01136 0.00457 -0.0224 0.1490 1.0000
6.750 1.0147 0.01163 0.00481 -0.0223 0.1420 1.0000
7.000 1.0421 0.01188 0.00506 -0.0222 0.1368 1.0000
7.250 1.0693 0.01217 0.00535 -0.0221 0.1322 1.0000
7.500 1.0964 0.01247 0.00566 -0.0220 0.1284 1.0000
7.750 1.1235 0.01275 0.00597 -0.0219 0.1250 1.0000
8.000 1.1503 0.01307 0.00631 -0.0218 0.1207 1.0000
8.250 1.1770 0.01343 0.00668 -0.0217 0.1167 1.0000
8.500 1.2037 0.01375 0.00706 -0.0216 0.1135 1.0000
8.750 1.2304 0.01405 0.00742 -0.0214 0.1100 1.0000
9.000 1.2567 0.01442 0.00783 -0.0213 0.1060 1.0000
9.250 1.2827 0.01487 0.00831 -0.0212 0.1012 1.0000
9.500 1.3091 0.01517 0.00869 -0.0210 0.0968 1.0000
9.750 1.3347 0.01565 0.00917 -0.0209 0.0859 1.0000
10.250 1.3815 0.01755 0.01088 -0.0207 0.0521 1.0000
10.500 1.4054 0.01831 0.01170 -0.0205 0.0477 1.0000
10.750 1.4295 0.01896 0.01242 -0.0203 0.0447 1.0000
11.000 1.4526 0.01977 0.01330 -0.0200 0.0416 1.0000
11.250 1.4756 0.02056 0.01417 -0.0198 0.0392 1.0000
11.500 1.4988 0.02125 0.01496 -0.0195 0.0372 1.0000
11.750 1.5208 0.02210 0.01589 -0.0193 0.0347 1.0000
12.000 1.5416 0.02313 0.01698 -0.0190 0.0324 1.0000
12.250 1.5633 0.02391 0.01787 -0.0187 0.0306 1.0000
12.500 1.5835 0.02488 0.01893 -0.0184 0.0284 1.0000
12.750 1.6020 0.02607 0.02020 -0.0180 0.0263 1.0000
13.000 1.6208 0.02711 0.02135 -0.0176 0.0240 1.0000
13.250 1.6364 0.02853 0.02283 -0.0173 0.0216 1.0000
13.500 1.6513 0.02993 0.02435 -0.0169 0.0195 1.0000
13.750 1.6623 0.03174 0.02626 -0.0165 0.0177 1.0000
14.000 1.6699 0.03384 0.02850 -0.0163 0.0164 1.0000
14.250 1.6694 0.03662 0.03144 -0.0162 0.0155 1.0000
14.500 1.6492 0.04487 0.03999 -0.0240 0.0155 1.0000
14.750 1.6139 0.05606 0.05144 -0.0325 0.0159 1.0000
15.000 1.5709 0.06649 0.06206 -0.0381 0.0166 1.0000
15.250 1.5291 0.07654 0.07226 -0.0430 0.0172 1.0000
15.500 1.4942 0.08558 0.08145 -0.0472 0.0176 1.0000
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