TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 200,000 Max Cl/Cd: 66.6 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi12-il-200000.txt Download as CSV file: xf-tsagi12-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4749 0.11199 0.10831 -0.0219 1.0000 0.0583
-11.000 -0.4961 0.10576 0.10217 -0.0300 1.0000 0.0605
-10.750 -0.5065 0.09993 0.09639 -0.0349 1.0000 0.0607
-10.500 -0.5075 0.09445 0.09094 -0.0339 1.0000 0.0622
-10.250 -0.4938 0.09287 0.08936 -0.0312 1.0000 0.0635
-10.000 -0.4920 0.08945 0.08596 -0.0318 1.0000 0.0647
-9.750 -0.4940 0.08554 0.08208 -0.0333 1.0000 0.0662
-9.500 -0.5039 0.08032 0.07691 -0.0368 1.0000 0.0670
-9.250 -0.5229 0.07444 0.07105 -0.0412 1.0000 0.0671
-9.000 -0.5446 0.07003 0.06662 -0.0416 1.0000 0.0680
-8.750 -0.5683 0.06662 0.06318 -0.0390 1.0000 0.0690
-8.500 -0.5867 0.06312 0.05959 -0.0364 1.0000 0.0701
-8.250 -0.6983 0.04424 0.03927 -0.0222 1.0000 0.0402
-8.000 -0.6976 0.04086 0.03576 -0.0187 1.0000 0.0392
-7.750 -0.7039 0.03775 0.03239 -0.0136 1.0000 0.0390
-7.500 -0.7097 0.03514 0.02949 -0.0083 1.0000 0.0389
-7.250 -0.7151 0.03292 0.02697 -0.0029 1.0000 0.0390
-7.000 -0.7175 0.03129 0.02503 0.0021 0.9998 0.0394
-6.750 -0.6870 0.02777 0.02109 0.0003 0.9940 0.0419
-6.500 -0.6510 0.02615 0.01929 -0.0019 0.9874 0.0442
-6.250 -0.6124 0.02413 0.01692 -0.0041 0.9824 0.0467
-6.000 -0.5764 0.02263 0.01505 -0.0057 0.9747 0.0504
-5.750 -0.5351 0.02105 0.01344 -0.0089 0.9704 0.0541
-5.500 -0.4967 0.02014 0.01238 -0.0109 0.9621 0.0591
-5.250 -0.4522 0.01863 0.01081 -0.0144 0.9571 0.0648
-5.000 -0.4105 0.01779 0.00989 -0.0172 0.9490 0.0719
-4.750 -0.3689 0.01643 0.00857 -0.0201 0.9421 0.0804
-4.500 -0.3343 0.01543 0.00759 -0.0215 0.9316 0.0920
-4.250 -0.3002 0.01451 0.00674 -0.0228 0.9215 0.1100
-4.000 -0.2679 0.01383 0.00612 -0.0237 0.9102 0.1328
-3.750 -0.2410 0.01330 0.00568 -0.0235 0.8962 0.1608
-3.500 -0.2187 0.01264 0.00528 -0.0224 0.8819 0.2127
-3.250 -0.2018 0.01186 0.00493 -0.0203 0.8678 0.3147
-3.000 -0.1957 0.01083 0.00467 -0.0159 0.8536 0.4918
-2.750 -0.1085 0.01025 0.00540 -0.0262 0.8492 0.8503
-2.500 -0.0701 0.01074 0.00574 -0.0273 0.8366 0.8793
-2.250 -0.0331 0.01126 0.00609 -0.0282 0.8243 0.8973
-2.000 0.0128 0.01184 0.00649 -0.0309 0.8129 0.9117
-1.750 0.0613 0.01231 0.00678 -0.0343 0.8015 0.9231
-1.500 0.1083 0.01269 0.00700 -0.0376 0.7894 0.9351
-1.250 0.1482 0.01292 0.00710 -0.0398 0.7767 0.9458
-1.000 0.1936 0.01305 0.00711 -0.0431 0.7642 0.9547
-0.750 0.2544 0.01325 0.00718 -0.0495 0.7516 0.9714
-0.500 0.3320 0.01284 0.00664 -0.0595 0.7385 0.9889
-0.250 0.3726 0.01255 0.00624 -0.0624 0.7252 0.9958
0.000 0.4075 0.01227 0.00586 -0.0642 0.7123 1.0000
0.250 0.4277 0.01222 0.00576 -0.0630 0.6990 1.0000
0.500 0.4481 0.01219 0.00566 -0.0618 0.6859 1.0000
0.750 0.4688 0.01218 0.00559 -0.0607 0.6729 1.0000
1.000 0.4897 0.01218 0.00553 -0.0595 0.6604 1.0000
1.250 0.5108 0.01220 0.00548 -0.0584 0.6480 1.0000
1.500 0.5321 0.01224 0.00544 -0.0572 0.6360 1.0000
1.750 0.5532 0.01227 0.00544 -0.0561 0.6232 1.0000
2.000 0.5746 0.01231 0.00547 -0.0550 0.6107 1.0000
2.250 0.5961 0.01238 0.00551 -0.0539 0.5990 1.0000
2.500 0.6179 0.01245 0.00554 -0.0529 0.5879 1.0000
2.750 0.6397 0.01253 0.00558 -0.0518 0.5771 1.0000
3.000 0.6613 0.01261 0.00568 -0.0508 0.5656 1.0000
3.250 0.6832 0.01270 0.00577 -0.0497 0.5552 1.0000
3.500 0.7054 0.01281 0.00583 -0.0487 0.5459 1.0000
3.750 0.7270 0.01290 0.00598 -0.0477 0.5348 1.0000
4.000 0.7490 0.01302 0.00612 -0.0466 0.5251 1.0000
4.250 0.7713 0.01316 0.00622 -0.0456 0.5161 1.0000
4.500 0.7927 0.01326 0.00640 -0.0445 0.5052 1.0000
4.750 0.8141 0.01339 0.00657 -0.0433 0.4943 1.0000
5.000 0.8357 0.01354 0.00672 -0.0422 0.4839 1.0000
5.250 0.8571 0.01369 0.00689 -0.0410 0.4730 1.0000
5.500 0.8775 0.01382 0.00707 -0.0396 0.4598 1.0000
5.750 0.8968 0.01395 0.00717 -0.0380 0.4427 1.0000
6.000 0.9153 0.01406 0.00733 -0.0363 0.4232 1.0000
6.250 0.9342 0.01422 0.00753 -0.0346 0.4057 1.0000
6.500 0.9524 0.01439 0.00771 -0.0329 0.3856 1.0000
6.750 0.9702 0.01458 0.00795 -0.0311 0.3636 1.0000
7.000 0.9870 0.01482 0.00820 -0.0291 0.3378 1.0000
7.250 1.0023 0.01515 0.00850 -0.0269 0.2986 1.0000
7.500 1.0085 0.01607 0.00904 -0.0234 0.2234 1.0000
7.750 0.9977 0.01829 0.01039 -0.0177 0.1015 1.0000
8.000 0.9930 0.02004 0.01181 -0.0125 0.0625 1.0000
8.250 0.9964 0.02113 0.01288 -0.0085 0.0523 1.0000
8.500 0.9994 0.02213 0.01396 -0.0044 0.0476 1.0000
8.750 1.0015 0.02307 0.01495 -0.0003 0.0441 1.0000
9.000 0.9965 0.02416 0.01604 0.0048 0.0418 1.0000
9.250 0.9883 0.02518 0.01712 0.0106 0.0398 1.0000
9.500 0.9862 0.02616 0.01818 0.0150 0.0384 1.0000
9.750 0.9854 0.02731 0.01939 0.0188 0.0372 1.0000
10.000 0.9860 0.02859 0.02072 0.0221 0.0358 1.0000
10.250 0.9882 0.02998 0.02213 0.0250 0.0346 1.0000
10.500 0.9928 0.03151 0.02367 0.0274 0.0335 1.0000
10.750 1.0038 0.03351 0.02567 0.0294 0.0318 1.0000
11.000 1.0136 0.03474 0.02704 0.0313 0.0309 1.0000
11.250 1.0256 0.03618 0.02859 0.0330 0.0300 1.0000
11.500 1.0388 0.03781 0.03035 0.0345 0.0290 1.0000
11.750 1.0523 0.03960 0.03229 0.0360 0.0285 1.0000
12.000 1.0636 0.04157 0.03442 0.0375 0.0280 1.0000
12.250 1.0725 0.04370 0.03672 0.0390 0.0275 1.0000
12.500 1.0789 0.04601 0.03920 0.0405 0.0270 1.0000
12.750 1.0811 0.04831 0.04167 0.0420 0.0267 1.0000
13.000 1.0828 0.05076 0.04423 0.0433 0.0261 1.0000
13.250 1.0822 0.05370 0.04734 0.0445 0.0258 1.0000
13.500 1.0785 0.05717 0.05097 0.0455 0.0254 1.0000
13.750 1.0683 0.06109 0.05511 0.0464 0.0252 1.0000
14.000 1.0558 0.06392 0.05817 0.0469 0.0256 1.0000
14.250 1.0425 0.06801 0.06245 0.0470 0.0254 1.0000
14.500 1.0253 0.07205 0.06673 0.0463 0.0258 1.0000
14.750 1.0047 0.07712 0.07203 0.0451 0.0259 1.0000
15.000 0.9495 0.08708 0.08249 0.0401 0.0274 1.0000
15.250 0.9186 0.09526 0.09090 0.0358 0.0279 1.0000
15.500 0.8880 0.10420 0.10003 0.0307 0.0281 1.0000
15.750 0.8485 0.11622 0.11222 0.0236 0.0293 1.0000
16.000 0.8123 0.12897 0.12507 0.0163 0.0304 1.0000
16.250 0.7963 0.13716 0.13326 0.0131 0.0317 1.0000
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