GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.61 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe235-il-1000000-n5.txt Download as CSV file: xf-goe235-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 235 (SCHTTE-LANZ) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4954 0.10620 0.10449 0.0096 1.0000 0.0140
-9.000 -0.4900 0.10269 0.10099 0.0078 1.0000 0.0142
-8.750 -0.4945 0.09617 0.09447 0.0038 1.0000 0.0152
-8.500 -0.4859 0.09371 0.09202 0.0025 1.0000 0.0153
-8.250 -0.4772 0.09121 0.08953 0.0010 1.0000 0.0154
-8.000 -0.4690 0.08856 0.08690 -0.0008 1.0000 0.0155
-7.750 -0.4574 0.08538 0.08371 -0.0042 0.9599 0.0156
-7.500 -0.4479 0.08227 0.08053 -0.0070 0.9260 0.0158
-7.250 -0.4379 0.07906 0.07719 -0.0099 0.8800 0.0159
-7.000 -0.4239 0.07548 0.07347 -0.0139 0.8527 0.0161
-6.500 -0.3879 0.06750 0.06531 -0.0236 0.8244 0.0166
-6.250 -0.3666 0.06314 0.06085 -0.0288 0.8144 0.0169
-6.000 -0.3381 0.05381 0.05133 -0.0397 0.8069 0.0180
-5.750 -0.3144 0.05076 0.04818 -0.0426 0.7975 0.0182
-5.500 -0.2901 0.04822 0.04555 -0.0448 0.7874 0.0183
-5.250 -0.2646 0.04547 0.04271 -0.0471 0.7773 0.0184
-5.000 -0.2383 0.04263 0.03974 -0.0494 0.7662 0.0186
-4.750 -0.2112 0.03965 0.03662 -0.0516 0.7520 0.0187
-4.500 -0.1838 0.03701 0.03382 -0.0533 0.7332 0.0191
-4.250 -0.1558 0.03405 0.03063 -0.0550 0.7021 0.0195
-4.000 -0.1268 0.03053 0.02679 -0.0567 0.6702 0.0198
-3.750 -0.0970 0.02646 0.02238 -0.0581 0.6537 0.0203
-3.500 -0.0673 0.02206 0.01755 -0.0591 0.6428 0.0206
-3.250 -0.0377 0.01623 0.01104 -0.0599 0.6351 0.0215
-3.000 -0.0097 0.01541 0.01006 -0.0600 0.6251 0.0217
-2.750 0.0184 0.01464 0.00913 -0.0601 0.6151 0.0219
-2.500 0.0467 0.01384 0.00818 -0.0602 0.6050 0.0222
-2.250 0.0751 0.01283 0.00699 -0.0602 0.5962 0.0226
-2.000 0.1036 0.01152 0.00545 -0.0603 0.5882 0.0231
-1.750 0.1319 0.01066 0.00441 -0.0603 0.5768 0.0235
-1.500 0.1603 0.01013 0.00376 -0.0602 0.5624 0.0239
-1.250 0.1885 0.00983 0.00333 -0.0602 0.5380 0.0243
-1.000 0.2159 0.01002 0.00309 -0.0602 0.4323 0.0246
-0.750 0.2437 0.01001 0.00283 -0.0602 0.3765 0.0249
-0.500 0.2715 0.00993 0.00254 -0.0603 0.3267 0.0254
-0.250 0.2988 0.01029 0.00251 -0.0604 0.2257 0.0257
0.000 0.3270 0.01029 0.00244 -0.0604 0.2076 0.0261
0.250 0.3552 0.01027 0.00236 -0.0603 0.1931 0.0266
0.500 0.3834 0.01025 0.00228 -0.0603 0.1819 0.0270
0.750 0.4117 0.01020 0.00221 -0.0603 0.1754 0.0275
1.000 0.4400 0.01018 0.00215 -0.0603 0.1680 0.0280
1.250 0.4683 0.01015 0.00210 -0.0602 0.1639 0.0286
1.500 0.4965 0.01016 0.00208 -0.0602 0.1578 0.0291
1.750 0.5247 0.01016 0.00206 -0.0602 0.1511 0.0302
2.000 0.5528 0.01022 0.00209 -0.0601 0.1405 0.0312
2.250 0.5790 0.01086 0.00236 -0.0600 0.0460 0.0321
2.500 0.6067 0.01102 0.00247 -0.0599 0.0336 0.0331
2.750 0.6346 0.01112 0.00256 -0.0599 0.0315 0.0341
3.000 0.6624 0.01122 0.00268 -0.0598 0.0299 0.0360
3.250 0.6902 0.01134 0.00281 -0.0597 0.0291 0.0383
3.500 0.7179 0.01145 0.00295 -0.0596 0.0287 0.0417
3.750 0.7455 0.01159 0.00310 -0.0594 0.0282 0.0454
4.000 0.7731 0.01173 0.00327 -0.0593 0.0277 0.0507
4.250 0.8005 0.01189 0.00345 -0.0592 0.0272 0.0583
4.500 0.8238 0.01030 0.00383 -0.0587 0.0268 1.0000
4.750 0.8510 0.01054 0.00405 -0.0586 0.0264 1.0000
5.000 0.8781 0.01080 0.00429 -0.0584 0.0259 1.0000
5.250 0.9050 0.01109 0.00456 -0.0582 0.0254 1.0000
5.500 0.9316 0.01143 0.00490 -0.0580 0.0247 1.0000
5.750 0.9579 0.01183 0.00531 -0.0577 0.0243 1.0000
6.000 0.9846 0.01211 0.00559 -0.0575 0.0241 1.0000
6.250 1.0111 0.01241 0.00590 -0.0573 0.0240 1.0000
6.500 1.0374 0.01273 0.00623 -0.0570 0.0238 1.0000
6.750 1.0635 0.01307 0.00658 -0.0567 0.0235 1.0000
7.000 1.0894 0.01342 0.00695 -0.0565 0.0233 1.0000
7.250 1.1151 0.01380 0.00736 -0.0561 0.0230 1.0000
7.500 1.1406 0.01419 0.00776 -0.0558 0.0227 1.0000
7.750 1.1660 0.01457 0.00816 -0.0555 0.0224 1.0000
8.000 1.1911 0.01497 0.00858 -0.0551 0.0220 1.0000
8.250 1.2159 0.01540 0.00904 -0.0547 0.0218 1.0000
8.500 1.2405 0.01585 0.00951 -0.0543 0.0215 1.0000
8.750 1.2647 0.01631 0.00999 -0.0539 0.0212 1.0000
9.000 1.2887 0.01679 0.01051 -0.0534 0.0210 1.0000
9.250 1.3122 0.01731 0.01104 -0.0529 0.0207 1.0000
9.500 1.3348 0.01792 0.01168 -0.0522 0.0204 1.0000
9.750 1.3550 0.01880 0.01262 -0.0514 0.0200 1.0000
10.000 1.3779 0.01930 0.01316 -0.0508 0.0199 1.0000
10.250 1.4002 0.01983 0.01374 -0.0501 0.0197 1.0000
10.500 1.4221 0.02039 0.01435 -0.0494 0.0195 1.0000
10.750 1.4437 0.02094 0.01495 -0.0487 0.0193 1.0000
11.000 1.4650 0.02149 0.01556 -0.0479 0.0189 1.0000
11.250 1.4855 0.02209 0.01622 -0.0471 0.0186 1.0000
11.500 1.5050 0.02275 0.01693 -0.0462 0.0184 1.0000
11.750 1.5240 0.02342 0.01766 -0.0452 0.0181 1.0000
12.000 1.5428 0.02405 0.01834 -0.0442 0.0178 1.0000
12.250 1.5616 0.02463 0.01896 -0.0432 0.0176 1.0000
12.500 1.5800 0.02519 0.01957 -0.0422 0.0173 1.0000
12.750 1.5969 0.02582 0.02024 -0.0410 0.0171 1.0000
13.000 1.6104 0.02654 0.02101 -0.0393 0.0169 1.0000
13.250 1.6205 0.02741 0.02194 -0.0373 0.0167 1.0000
13.500 1.6279 0.02855 0.02314 -0.0352 0.0165 1.0000
13.750 1.6331 0.02996 0.02464 -0.0333 0.0163 1.0000
14.000 1.6421 0.03119 0.02596 -0.0320 0.0162 1.0000
14.250 1.6503 0.03258 0.02745 -0.0309 0.0160 1.0000
14.500 1.6577 0.03415 0.02911 -0.0300 0.0158 1.0000
14.750 1.6636 0.03594 0.03099 -0.0293 0.0156 1.0000
15.000 1.6687 0.03791 0.03307 -0.0288 0.0154 1.0000
15.250 1.6724 0.04011 0.03536 -0.0284 0.0152 1.0000
15.500 1.6755 0.04249 0.03784 -0.0282 0.0150 1.0000
15.750 1.6777 0.04508 0.04053 -0.0283 0.0148 1.0000
16.000 1.6788 0.04791 0.04346 -0.0287 0.0146 1.0000
16.250 1.6788 0.05103 0.04667 -0.0293 0.0145 1.0000
16.500 1.6777 0.05437 0.05011 -0.0301 0.0143 1.0000
16.750 1.6750 0.05798 0.05381 -0.0310 0.0142 1.0000
17.000 1.6708 0.06189 0.05782 -0.0322 0.0140 1.0000
17.250 1.6638 0.06634 0.06237 -0.0337 0.0139 1.0000
17.500 1.6540 0.07138 0.06751 -0.0356 0.0138 1.0000
17.750 1.6416 0.07714 0.07339 -0.0381 0.0137 1.0000
18.000 1.6253 0.08371 0.08009 -0.0410 0.0136 1.0000
18.250 1.6070 0.09071 0.08721 -0.0441 0.0135 1.0000
18.500 1.5858 0.09832 0.09495 -0.0476 0.0135 1.0000
18.750 1.5646 0.10599 0.10273 -0.0511 0.0134 1.0000
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