AG35 (ag35-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 200,000 Max Cl/Cd: 65.34 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag35-il-200000-n5.txt Download as CSV file: xf-ag35-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG35
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5159 0.11195 0.10834 0.0022 1.0000 0.0180
-11.000 -0.5248 0.09848 0.09495 -0.0054 1.0000 0.0154
-10.500 -0.5235 0.08983 0.08637 -0.0100 1.0000 0.0158
-10.250 -0.5150 0.08815 0.08470 -0.0106 1.0000 0.0166
-10.000 -0.5133 0.08416 0.08074 -0.0132 1.0000 0.0170
-9.750 -0.5141 0.07958 0.07620 -0.0166 1.0000 0.0173
-9.500 -0.5151 0.07375 0.07041 -0.0226 1.0000 0.0173
-9.250 -0.5133 0.06611 0.06274 -0.0307 1.0000 0.0171
-9.000 -0.5318 0.04434 0.04037 -0.0449 1.0000 0.0157
-8.750 -0.5267 0.03761 0.03312 -0.0463 1.0000 0.0157
-8.500 -0.5148 0.03342 0.02852 -0.0463 1.0000 0.0159
-8.250 -0.4994 0.03041 0.02515 -0.0457 1.0000 0.0163
-8.000 -0.4825 0.02788 0.02228 -0.0448 1.0000 0.0167
-7.750 -0.4644 0.02568 0.01974 -0.0438 1.0000 0.0172
-7.500 -0.4452 0.02393 0.01768 -0.0427 1.0000 0.0180
-7.250 -0.4254 0.02239 0.01580 -0.0414 1.0000 0.0193
-7.000 -0.3938 0.02055 0.01351 -0.0424 0.9960 0.0203
-6.750 -0.3606 0.01869 0.01137 -0.0437 0.9910 0.0211
-6.500 -0.3269 0.01745 0.01002 -0.0451 0.9858 0.0222
-6.250 -0.2930 0.01649 0.00895 -0.0464 0.9799 0.0236
-6.000 -0.2592 0.01575 0.00809 -0.0476 0.9727 0.0260
-5.750 -0.2266 0.01486 0.00711 -0.0486 0.9653 0.0282
-5.500 -0.1938 0.01411 0.00631 -0.0496 0.9577 0.0307
-5.250 -0.1620 0.01354 0.00568 -0.0503 0.9482 0.0341
-5.000 -0.1298 0.01297 0.00508 -0.0512 0.9393 0.0396
-4.750 -0.0992 0.01255 0.00457 -0.0516 0.9289 0.0459
-4.500 -0.0696 0.01211 0.00414 -0.0517 0.9168 0.0580
-4.250 -0.0409 0.01167 0.00377 -0.0518 0.9044 0.0793
-4.000 -0.0130 0.01123 0.00349 -0.0517 0.8917 0.1234
-3.750 0.0140 0.01078 0.00326 -0.0515 0.8785 0.1918
-3.250 0.0662 0.00995 0.00296 -0.0507 0.8494 0.3631
-3.000 0.0910 0.00945 0.00283 -0.0500 0.8331 0.4794
-2.750 0.1131 0.00883 0.00277 -0.0485 0.8163 0.6422
-2.500 0.1324 0.00832 0.00276 -0.0456 0.7998 0.8176
-2.250 0.1721 0.00817 0.00266 -0.0470 0.7823 0.9553
-2.000 0.2137 0.00818 0.00251 -0.0497 0.7625 1.0000
-1.750 0.2394 0.00826 0.00242 -0.0491 0.7414 1.0000
-1.500 0.2652 0.00835 0.00234 -0.0485 0.7190 1.0000
-1.250 0.2912 0.00845 0.00228 -0.0480 0.6934 1.0000
-1.000 0.3172 0.00855 0.00223 -0.0475 0.6610 1.0000
-0.750 0.3427 0.00871 0.00216 -0.0469 0.6290 1.0000
-0.500 0.3684 0.00891 0.00214 -0.0463 0.6068 1.0000
-0.250 0.3946 0.00911 0.00218 -0.0459 0.5877 1.0000
0.000 0.4210 0.00931 0.00224 -0.0456 0.5711 1.0000
0.250 0.4476 0.00950 0.00233 -0.0454 0.5567 1.0000
0.500 0.4744 0.00968 0.00243 -0.0452 0.5436 1.0000
0.750 0.5012 0.00987 0.00254 -0.0450 0.5313 1.0000
1.000 0.5281 0.01005 0.00266 -0.0448 0.5188 1.0000
1.250 0.5551 0.01021 0.00280 -0.0447 0.5060 1.0000
1.500 0.5821 0.01038 0.00294 -0.0446 0.4931 1.0000
1.750 0.6091 0.01055 0.00309 -0.0444 0.4795 1.0000
2.000 0.6360 0.01071 0.00325 -0.0443 0.4648 1.0000
2.250 0.6629 0.01088 0.00342 -0.0442 0.4485 1.0000
2.500 0.6894 0.01108 0.00358 -0.0440 0.4305 1.0000
2.750 0.7159 0.01128 0.00376 -0.0439 0.4097 1.0000
3.000 0.7420 0.01154 0.00397 -0.0437 0.3865 1.0000
3.250 0.7678 0.01183 0.00420 -0.0434 0.3607 1.0000
3.500 0.7934 0.01216 0.00446 -0.0432 0.3342 1.0000
3.750 0.8187 0.01253 0.00475 -0.0430 0.3074 1.0000
4.000 0.8438 0.01294 0.00510 -0.0427 0.2812 1.0000
4.250 0.8687 0.01338 0.00547 -0.0425 0.2567 1.0000
4.500 0.8934 0.01384 0.00588 -0.0423 0.2334 1.0000
4.750 0.9181 0.01431 0.00631 -0.0420 0.2123 1.0000
5.000 0.9425 0.01482 0.00679 -0.0417 0.1915 1.0000
5.250 0.9667 0.01534 0.00728 -0.0415 0.1721 1.0000
5.500 0.9906 0.01587 0.00779 -0.0412 0.1521 1.0000
5.750 1.0140 0.01648 0.00835 -0.0408 0.1324 1.0000
6.000 1.0372 0.01710 0.00896 -0.0405 0.1125 1.0000
6.250 1.0595 0.01782 0.00961 -0.0400 0.0940 1.0000
6.500 1.0818 0.01853 0.01031 -0.0396 0.0775 1.0000
6.750 1.1034 0.01931 0.01107 -0.0391 0.0629 1.0000
7.000 1.1243 0.02015 0.01190 -0.0385 0.0503 1.0000
7.250 1.1445 0.02105 0.01284 -0.0378 0.0403 1.0000
7.500 1.1639 0.02202 0.01384 -0.0370 0.0325 1.0000
7.750 1.1818 0.02312 0.01498 -0.0361 0.0273 1.0000
8.000 1.1998 0.02415 0.01614 -0.0351 0.0237 1.0000
8.250 1.2148 0.02546 0.01751 -0.0339 0.0209 1.0000
8.500 1.2311 0.02654 0.01874 -0.0327 0.0187 1.0000
8.750 1.2452 0.02776 0.02010 -0.0315 0.0171 1.0000
9.000 1.2544 0.02935 0.02180 -0.0298 0.0160 1.0000
9.250 1.2632 0.03087 0.02348 -0.0279 0.0152 1.0000
9.500 1.2688 0.03238 0.02515 -0.0257 0.0146 1.0000
9.750 1.2730 0.03408 0.02700 -0.0236 0.0140 1.0000
10.000 1.2765 0.03591 0.02898 -0.0220 0.0134 1.0000
10.250 1.2794 0.03788 0.03109 -0.0207 0.0128 1.0000
10.500 1.2809 0.04011 0.03345 -0.0197 0.0123 1.0000
10.750 1.2798 0.04276 0.03621 -0.0192 0.0119 1.0000
11.000 1.2748 0.04604 0.03963 -0.0189 0.0115 1.0000
11.250 1.2745 0.04902 0.04283 -0.0190 0.0112 1.0000
11.500 1.2718 0.05245 0.04646 -0.0195 0.0110 1.0000
11.750 1.2672 0.05630 0.05050 -0.0204 0.0107 1.0000
12.000 1.2612 0.06054 0.05494 -0.0216 0.0106 1.0000
12.250 1.2540 0.06515 0.05974 -0.0232 0.0104 1.0000
12.500 1.2450 0.07012 0.06489 -0.0251 0.0103 1.0000
12.750 1.2346 0.07546 0.07041 -0.0273 0.0102 1.0000
13.000 1.2226 0.08118 0.07631 -0.0298 0.0101 1.0000
13.250 1.2092 0.08732 0.08263 -0.0326 0.0100 1.0000
13.500 1.1949 0.09393 0.08941 -0.0358 0.0100 1.0000
13.750 1.1795 0.10101 0.09666 -0.0394 0.0100 1.0000
14.000 1.1631 0.10864 0.10446 -0.0433 0.0100 1.0000
14.250 1.1458 0.11682 0.11281 -0.0476 0.0100 1.0000
14.500 1.1276 0.12559 0.12174 -0.0523 0.0101 1.0000
14.750 1.1078 0.13521 0.13151 -0.0576 0.0102 1.0000
15.000 1.0852 0.14612 0.14257 -0.0635 0.0103 1.0000
15.250 1.0565 0.15959 0.15615 -0.0708 0.0106 1.0000
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