TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 200,000 Max Cl/Cd: 65.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi12-il-200000-n5.txt Download as CSV file: xf-tsagi12-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 12% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6907 0.05982 0.05611 -0.0510 1.0000 0.0137
-11.500 -0.7197 0.05325 0.04936 -0.0544 1.0000 0.0136
-11.250 -0.7474 0.04850 0.04440 -0.0538 1.0000 0.0135
-11.000 -0.7711 0.04482 0.04047 -0.0508 1.0000 0.0135
-10.750 -0.7905 0.04186 0.03726 -0.0464 1.0000 0.0135
-10.500 -0.8090 0.03909 0.03414 -0.0410 1.0000 0.0138
-10.250 -0.8187 0.03655 0.03134 -0.0365 1.0000 0.0141
-10.000 -0.8188 0.03477 0.02939 -0.0330 1.0000 0.0144
-9.750 -0.8132 0.03357 0.02808 -0.0300 1.0000 0.0149
-9.500 -0.8047 0.03264 0.02706 -0.0272 1.0000 0.0154
-9.250 -0.7972 0.03142 0.02567 -0.0243 1.0000 0.0161
-9.000 -0.7909 0.02978 0.02378 -0.0210 1.0000 0.0167
-8.750 -0.7834 0.02812 0.02185 -0.0177 1.0000 0.0174
-8.500 -0.7744 0.02660 0.02006 -0.0146 1.0000 0.0182
-8.250 -0.7641 0.02527 0.01848 -0.0116 1.0000 0.0190
-8.000 -0.7481 0.02397 0.01701 -0.0099 0.9982 0.0199
-7.750 -0.7166 0.02320 0.01617 -0.0114 0.9906 0.0218
-7.500 -0.6848 0.02213 0.01492 -0.0127 0.9833 0.0239
-7.250 -0.6529 0.02098 0.01353 -0.0138 0.9755 0.0258
-7.000 -0.6232 0.01984 0.01232 -0.0147 0.9665 0.0284
-6.750 -0.5901 0.01912 0.01149 -0.0162 0.9581 0.0317
-6.500 -0.5560 0.01834 0.01053 -0.0176 0.9492 0.0346
-6.250 -0.5250 0.01751 0.00971 -0.0187 0.9380 0.0387
-6.000 -0.4914 0.01692 0.00902 -0.0201 0.9270 0.0427
-5.750 -0.4583 0.01628 0.00834 -0.0214 0.9149 0.0470
-5.500 -0.4251 0.01583 0.00780 -0.0226 0.9005 0.0521
-5.250 -0.3941 0.01534 0.00722 -0.0233 0.8828 0.0575
-5.000 -0.3649 0.01491 0.00670 -0.0235 0.8633 0.0637
-4.750 -0.3384 0.01451 0.00618 -0.0232 0.8454 0.0703
-4.500 -0.3133 0.01419 0.00575 -0.0226 0.8301 0.0794
-4.250 -0.2897 0.01383 0.00535 -0.0217 0.8161 0.0882
-4.000 -0.2659 0.01355 0.00499 -0.0209 0.8027 0.0970
-3.750 -0.2425 0.01328 0.00469 -0.0200 0.7901 0.1080
-3.500 -0.2192 0.01301 0.00443 -0.0190 0.7781 0.1248
-3.250 -0.1962 0.01273 0.00420 -0.0181 0.7667 0.1537
-3.000 -0.1746 0.01237 0.00398 -0.0169 0.7554 0.2009
-2.750 -0.1541 0.01196 0.00377 -0.0156 0.7443 0.2605
-2.500 -0.1350 0.01152 0.00357 -0.0139 0.7341 0.3342
-2.250 -0.1199 0.01094 0.00338 -0.0114 0.7240 0.4424
-2.000 -0.1089 0.01022 0.00323 -0.0079 0.7138 0.5842
-1.750 -0.0596 0.00970 0.00344 -0.0118 0.7043 0.7827
-1.500 0.0053 0.00996 0.00366 -0.0190 0.6942 0.8474
-1.250 0.0444 0.01016 0.00378 -0.0210 0.6835 0.8682
-1.000 0.0763 0.01034 0.00385 -0.0216 0.6735 0.8827
-0.750 0.1076 0.01055 0.00395 -0.0220 0.6639 0.8964
-0.500 0.1441 0.01092 0.00424 -0.0232 0.6536 0.9127
-0.250 0.1903 0.01152 0.00474 -0.0262 0.6428 0.9334
0.000 0.2398 0.01197 0.00509 -0.0303 0.6321 0.9478
0.250 0.2734 0.01205 0.00510 -0.0315 0.6213 0.9529
0.500 0.3057 0.01207 0.00505 -0.0325 0.6105 0.9560
0.750 0.3344 0.01211 0.00501 -0.0328 0.6003 0.9599
1.000 0.3606 0.01216 0.00501 -0.0326 0.5896 0.9641
1.250 0.3932 0.01216 0.00496 -0.0338 0.5778 0.9663
1.500 0.4240 0.01218 0.00494 -0.0346 0.5668 0.9692
1.750 0.4522 0.01223 0.00494 -0.0348 0.5561 0.9726
2.000 0.4802 0.01228 0.00497 -0.0350 0.5445 0.9758
2.250 0.5120 0.01229 0.00495 -0.0361 0.5325 0.9781
2.500 0.5421 0.01233 0.00496 -0.0368 0.5213 0.9807
2.750 0.5705 0.01240 0.00500 -0.0371 0.5105 0.9837
3.000 0.5997 0.01246 0.00505 -0.0376 0.4995 0.9862
3.250 0.6309 0.01249 0.00509 -0.0385 0.4888 0.9884
3.500 0.6609 0.01256 0.00515 -0.0392 0.4785 0.9908
4.000 0.7203 0.01273 0.00534 -0.0405 0.4585 0.9955
4.250 0.7507 0.01281 0.00544 -0.0414 0.4490 0.9977
4.500 0.7807 0.01292 0.00556 -0.0421 0.4392 0.9997
4.750 0.8032 0.01306 0.00573 -0.0412 0.4274 1.0000
5.000 0.8246 0.01322 0.00593 -0.0401 0.4174 1.0000
5.250 0.8455 0.01341 0.00614 -0.0389 0.4077 1.0000
5.500 0.8665 0.01358 0.00637 -0.0378 0.3965 1.0000
5.750 0.8871 0.01376 0.00660 -0.0365 0.3836 1.0000
6.000 0.9071 0.01396 0.00684 -0.0351 0.3684 1.0000
6.250 0.9255 0.01420 0.00708 -0.0335 0.3435 1.0000
6.500 0.9420 0.01455 0.00732 -0.0316 0.3067 1.0000
6.750 0.9566 0.01506 0.00766 -0.0295 0.2635 1.0000
7.000 0.9687 0.01576 0.00814 -0.0270 0.2163 1.0000
7.250 0.9775 0.01672 0.00881 -0.0241 0.1630 1.0000
7.500 0.9844 0.01779 0.00960 -0.0209 0.1112 1.0000
7.750 0.9906 0.01885 0.01047 -0.0176 0.0763 1.0000
8.000 0.9961 0.01989 0.01135 -0.0142 0.0467 1.0000
8.250 1.0021 0.02082 0.01221 -0.0107 0.0352 1.0000
8.500 1.0092 0.02162 0.01306 -0.0074 0.0300 1.0000
8.750 1.0134 0.02252 0.01400 -0.0037 0.0267 1.0000
9.000 1.0192 0.02325 0.01482 -0.0002 0.0241 1.0000
9.250 1.0198 0.02401 0.01567 0.0042 0.0226 1.0000
9.500 1.0161 0.02485 0.01656 0.0090 0.0211 1.0000
9.750 1.0089 0.02603 0.01779 0.0139 0.0199 1.0000
10.000 1.0090 0.02707 0.01895 0.0174 0.0194 1.0000
10.250 1.0087 0.02831 0.02032 0.0206 0.0186 1.0000
10.500 1.0087 0.02970 0.02182 0.0233 0.0181 1.0000
10.750 1.0099 0.03117 0.02338 0.0255 0.0173 1.0000
11.000 1.0104 0.03283 0.02513 0.0275 0.0166 1.0000
11.250 1.0114 0.03459 0.02696 0.0291 0.0158 1.0000
11.500 1.0118 0.03651 0.02895 0.0305 0.0152 1.0000
11.750 1.0091 0.03882 0.03131 0.0319 0.0144 1.0000
12.000 1.0081 0.04108 0.03364 0.0331 0.0142 1.0000
12.250 1.0087 0.04330 0.03595 0.0342 0.0138 1.0000
12.500 1.0120 0.04531 0.03809 0.0351 0.0134 1.0000
12.750 1.0144 0.04749 0.04038 0.0360 0.0131 1.0000
13.000 1.0175 0.04964 0.04264 0.0367 0.0128 1.0000
13.250 1.0196 0.05195 0.04508 0.0373 0.0123 1.0000
13.500 1.0214 0.05435 0.04762 0.0376 0.0119 1.0000
13.750 1.0220 0.05691 0.05029 0.0377 0.0114 1.0000
14.000 1.0225 0.05955 0.05304 0.0378 0.0112 1.0000
14.250 1.0225 0.06233 0.05593 0.0377 0.0110 1.0000
14.500 1.0215 0.06528 0.05898 0.0374 0.0107 1.0000
14.750 1.0199 0.06842 0.06224 0.0370 0.0106 1.0000
15.000 1.0170 0.07181 0.06573 0.0365 0.0104 1.0000
15.250 1.0124 0.07551 0.06954 0.0358 0.0101 1.0000
15.500 1.0062 0.07959 0.07376 0.0350 0.0100 1.0000
15.750 0.9981 0.08414 0.07847 0.0336 0.0099 1.0000
16.000 0.9927 0.08837 0.08286 0.0322 0.0100 1.0000
16.250 0.9788 0.09427 0.08897 0.0297 0.0098 1.0000
16.500 0.9670 0.09996 0.09484 0.0273 0.0098 1.0000
16.750 0.9556 0.10571 0.10074 0.0247 0.0098 1.0000
17.000 0.9406 0.11251 0.10772 0.0213 0.0098 1.0000
17.250 0.9267 0.11920 0.11456 0.0180 0.0098 1.0000
17.500 0.9103 0.12687 0.12239 0.0139 0.0098 1.0000
17.750 0.8929 0.13515 0.13083 0.0094 0.0098 1.0000
18.000 0.8735 0.14437 0.14019 0.0044 0.0099 1.0000
18.250 0.8543 0.15409 0.15004 -0.0009 0.0099 1.0000
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