GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.69 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe54-il-1000000-n5.txt Download as CSV file: xf-goe54-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5666 0.09794 0.09643 0.0374 0.9771 0.0091
-8.000 -0.5640 0.09536 0.09304 0.0362 0.6898 0.0093
-7.750 -0.5618 0.08855 0.08615 0.0296 0.6613 0.0102
-7.500 -0.5476 0.08565 0.08299 0.0260 0.5728 0.0103
-7.250 -0.5318 0.08259 0.07974 0.0221 0.5147 0.0105
-7.000 -0.5147 0.07915 0.07620 0.0179 0.4871 0.0106
-6.750 -0.4961 0.07545 0.07242 0.0134 0.4709 0.0108
-6.000 -0.4270 0.06009 0.05675 -0.0039 0.4392 0.0126
-5.750 -0.4033 0.05751 0.05409 -0.0064 0.4289 0.0128
-5.500 -0.3782 0.05462 0.05111 -0.0090 0.4211 0.0130
-5.250 -0.3520 0.05150 0.04789 -0.0117 0.4139 0.0133
-5.000 -0.3246 0.04816 0.04440 -0.0144 0.4071 0.0137
-4.750 -0.2903 0.04179 0.03776 -0.0187 0.4030 0.0151
-4.500 -0.2645 0.03996 0.03585 -0.0197 0.3967 0.0153
-4.250 -0.2377 0.03808 0.03385 -0.0207 0.3906 0.0155
-4.000 -0.2099 0.03600 0.03166 -0.0217 0.3853 0.0157
-3.750 -0.1814 0.03378 0.02929 -0.0227 0.3790 0.0160
-3.500 -0.1521 0.03145 0.02679 -0.0235 0.3732 0.0164
-3.250 -0.1169 0.02715 0.02208 -0.0243 0.3681 0.0179
-3.000 -0.0898 0.02586 0.02069 -0.0247 0.3603 0.0181
-2.750 -0.0621 0.02470 0.01943 -0.0250 0.3529 0.0183
-2.500 -0.0338 0.02354 0.01812 -0.0253 0.3434 0.0185
-2.250 -0.0049 0.02224 0.01667 -0.0255 0.3335 0.0187
-2.000 0.0243 0.02096 0.01521 -0.0256 0.3214 0.0190
-1.750 0.0534 0.01989 0.01394 -0.0257 0.3023 0.0196
-1.500 0.0832 0.01863 0.01241 -0.0258 0.2790 0.0199
-1.250 0.1130 0.01745 0.01098 -0.0257 0.2614 0.0203
-1.000 0.1428 0.01632 0.00961 -0.0256 0.2498 0.0206
-0.750 0.1723 0.01536 0.00848 -0.0255 0.2429 0.0208
-0.500 0.2015 0.01445 0.00739 -0.0254 0.2368 0.0213
-0.250 0.2304 0.01374 0.00655 -0.0254 0.2312 0.0213
0.000 0.2591 0.01321 0.00595 -0.0253 0.2278 0.0215
0.250 0.2876 0.01283 0.00551 -0.0253 0.2236 0.0217
0.500 0.3161 0.01250 0.00511 -0.0252 0.2183 0.0220
0.750 0.3447 0.01216 0.00472 -0.0251 0.2141 0.0223
1.000 0.3733 0.01181 0.00433 -0.0250 0.2120 0.0227
1.250 0.4019 0.01147 0.00395 -0.0248 0.2092 0.0231
1.500 0.4304 0.01115 0.00360 -0.0247 0.2060 0.0233
1.750 0.4589 0.01089 0.00331 -0.0246 0.2029 0.0238
2.000 0.4874 0.01065 0.00304 -0.0245 0.2000 0.0242
2.250 0.5159 0.01040 0.00279 -0.0244 0.1980 0.0245
2.500 0.5444 0.01025 0.00264 -0.0244 0.1965 0.0248
2.750 0.5731 0.01004 0.00243 -0.0244 0.1945 0.0254
3.000 0.6016 0.01000 0.00240 -0.0243 0.1920 0.0259
3.250 0.6301 0.00998 0.00238 -0.0243 0.1891 0.0264
3.500 0.6585 0.00998 0.00238 -0.0242 0.1860 0.0269
3.750 0.6869 0.01000 0.00240 -0.0242 0.1830 0.0276
4.000 0.7153 0.01000 0.00242 -0.0241 0.1809 0.0286
4.250 0.7437 0.01002 0.00245 -0.0240 0.1777 0.0292
4.500 0.7720 0.01006 0.00249 -0.0240 0.1735 0.0297
4.750 0.8002 0.01012 0.00254 -0.0239 0.1689 0.0310
5.000 0.8284 0.01018 0.00262 -0.0239 0.1649 0.0323
5.250 0.8565 0.01030 0.00272 -0.0238 0.1574 0.0336
5.500 0.8843 0.01048 0.00285 -0.0237 0.1452 0.0356
5.750 0.9120 0.01070 0.00301 -0.0237 0.1336 0.0388
6.000 0.9397 0.01089 0.00320 -0.0236 0.1266 0.0447
6.500 0.9919 0.00967 0.00372 -0.0233 0.1200 1.0000
6.750 1.0195 0.00989 0.00394 -0.0232 0.1165 1.0000
7.000 1.0472 0.01009 0.00415 -0.0231 0.1143 1.0000
7.250 1.0748 0.01027 0.00435 -0.0230 0.1126 1.0000
7.500 1.1023 0.01049 0.00458 -0.0229 0.1102 1.0000
7.750 1.1295 0.01075 0.00484 -0.0228 0.1065 1.0000
8.000 1.1566 0.01104 0.00512 -0.0227 0.1022 1.0000
8.250 1.1840 0.01125 0.00537 -0.0226 0.1004 1.0000
8.500 1.2112 0.01146 0.00562 -0.0225 0.0979 1.0000
8.750 1.2381 0.01174 0.00591 -0.0225 0.0929 1.0000
9.000 1.2647 0.01208 0.00623 -0.0224 0.0863 1.0000
9.250 1.2890 0.01306 0.00699 -0.0223 0.0566 1.0000
9.500 1.3143 0.01370 0.00760 -0.0222 0.0480 1.0000
9.750 1.3402 0.01414 0.00807 -0.0220 0.0444 1.0000
10.000 1.3656 0.01468 0.00863 -0.0219 0.0408 1.0000
10.250 1.3913 0.01510 0.00909 -0.0217 0.0387 1.0000
10.500 1.4167 0.01555 0.00958 -0.0216 0.0367 1.0000
10.750 1.4415 0.01611 0.01017 -0.0214 0.0342 1.0000
11.000 1.4663 0.01664 0.01074 -0.0212 0.0322 1.0000
11.250 1.4912 0.01711 0.01126 -0.0210 0.0308 1.0000
11.500 1.5154 0.01768 0.01186 -0.0208 0.0287 1.0000
11.750 1.5389 0.01836 0.01257 -0.0206 0.0264 1.0000
12.000 1.5628 0.01892 0.01318 -0.0203 0.0244 1.0000
12.250 1.5854 0.01967 0.01396 -0.0201 0.0217 1.0000
12.500 1.6078 0.02040 0.01474 -0.0198 0.0191 1.0000
12.750 1.6290 0.02129 0.01565 -0.0195 0.0165 1.0000
13.000 1.6494 0.02226 0.01667 -0.0191 0.0144 1.0000
13.250 1.6694 0.02323 0.01770 -0.0187 0.0129 1.0000
13.500 1.6880 0.02432 0.01886 -0.0183 0.0116 1.0000
13.750 1.7056 0.02549 0.02011 -0.0178 0.0106 1.0000
14.000 1.7228 0.02662 0.02133 -0.0173 0.0100 1.0000
14.250 1.7379 0.02793 0.02274 -0.0168 0.0094 1.0000
14.500 1.7501 0.02950 0.02441 -0.0162 0.0088 1.0000
14.750 1.7584 0.03141 0.02643 -0.0157 0.0083 1.0000
15.000 1.7634 0.03350 0.02866 -0.0152 0.0080 1.0000
15.250 1.7530 0.03706 0.03239 -0.0156 0.0079 1.0000
15.500 1.7154 0.05075 0.04643 -0.0292 0.0081 1.0000
15.750 1.6590 0.06353 0.05943 -0.0364 0.0084 1.0000
16.000 1.6081 0.07480 0.07089 -0.0418 0.0088 1.0000
16.250 1.5624 0.08543 0.08168 -0.0467 0.0091 1.0000
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Polar data table (+)
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