TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 500,000 Max Cl/Cd: 88.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi12-il-500000.txt Download as CSV file: xf-tsagi12-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7297 0.05526 0.05270 -0.0537 1.0000 0.0144
-11.750 -0.7672 0.04838 0.04552 -0.0561 1.0000 0.0147
-11.500 -0.7955 0.04411 0.04106 -0.0541 1.0000 0.0145
-11.250 -0.8161 0.04106 0.03780 -0.0504 1.0000 0.0145
-11.000 -0.8375 0.03834 0.03480 -0.0450 1.0000 0.0147
-10.750 -0.8572 0.03578 0.03201 -0.0388 1.0000 0.0146
-10.500 -0.8576 0.03463 0.03059 -0.0347 1.0000 0.0150
-10.250 -0.8751 0.03091 0.02650 -0.0288 1.0000 0.0153
-10.000 -0.8755 0.02874 0.02413 -0.0248 1.0000 0.0156
-9.750 -0.8691 0.02731 0.02257 -0.0215 1.0000 0.0159
-9.500 -0.8588 0.02645 0.02161 -0.0187 1.0000 0.0163
-9.250 -0.8504 0.02521 0.02021 -0.0155 1.0000 0.0165
-9.000 -0.8390 0.02458 0.01950 -0.0127 1.0000 0.0172
-8.750 -0.8304 0.02349 0.01825 -0.0093 1.0000 0.0178
-8.500 -0.8222 0.02246 0.01707 -0.0058 1.0000 0.0182
-8.250 -0.8010 0.02155 0.01597 -0.0048 0.9986 0.0190
-8.000 -0.7693 0.01966 0.01385 -0.0063 0.9949 0.0201
-7.750 -0.7358 0.01878 0.01294 -0.0081 0.9904 0.0213
-7.500 -0.7005 0.01811 0.01220 -0.0100 0.9859 0.0227
-7.250 -0.6646 0.01733 0.01130 -0.0118 0.9817 0.0242
-7.000 -0.6334 0.01604 0.00987 -0.0128 0.9750 0.0256
-6.750 -0.5973 0.01517 0.00899 -0.0149 0.9703 0.0279
-6.500 -0.5618 0.01462 0.00838 -0.0167 0.9611 0.0302
-6.250 -0.5239 0.01377 0.00744 -0.0190 0.9518 0.0324
-6.000 -0.4870 0.01295 0.00659 -0.0212 0.9382 0.0358
-5.750 -0.4523 0.01251 0.00607 -0.0227 0.9206 0.0388
-5.500 -0.4240 0.01193 0.00540 -0.0228 0.9007 0.0421
-5.250 -0.3977 0.01160 0.00501 -0.0224 0.8812 0.0459
-5.000 -0.3724 0.01144 0.00473 -0.0218 0.8628 0.0495
-4.750 -0.3500 0.01109 0.00436 -0.0206 0.8452 0.0558
-4.500 -0.3264 0.01090 0.00409 -0.0196 0.8295 0.0631
-4.250 -0.3026 0.01073 0.00387 -0.0187 0.8150 0.0736
-4.000 -0.2804 0.01044 0.00354 -0.0175 0.8012 0.0857
-3.750 -0.2574 0.01022 0.00329 -0.0164 0.7883 0.0960
-3.500 -0.2341 0.01002 0.00308 -0.0155 0.7760 0.1074
-3.250 -0.2109 0.00979 0.00290 -0.0145 0.7643 0.1277
-3.000 -0.1886 0.00951 0.00273 -0.0134 0.7534 0.1681
-2.750 -0.1671 0.00919 0.00257 -0.0122 0.7428 0.2226
-2.500 -0.1465 0.00880 0.00241 -0.0108 0.7320 0.2943
-2.250 -0.1291 0.00828 0.00225 -0.0088 0.7225 0.3981
-2.000 -0.1191 0.00756 0.00208 -0.0052 0.7132 0.5503
-1.750 -0.1160 0.00673 0.00202 0.0003 0.7038 0.7423
-1.500 -0.0733 0.00659 0.00222 -0.0024 0.6948 0.8616
-1.250 -0.0306 0.00674 0.00234 -0.0053 0.6852 0.8904
-1.000 0.0074 0.00690 0.00244 -0.0073 0.6760 0.9043
-0.750 0.0357 0.00707 0.00251 -0.0071 0.6670 0.9158
-0.500 0.0793 0.00731 0.00268 -0.0103 0.6566 0.9208
-0.250 0.1058 0.00751 0.00282 -0.0097 0.6476 0.9302
0.000 0.1501 0.00784 0.00305 -0.0129 0.6374 0.9330
0.250 0.1941 0.00820 0.00335 -0.0161 0.6262 0.9384
0.500 0.2312 0.00852 0.00361 -0.0178 0.6160 0.9457
0.750 0.2895 0.00902 0.00403 -0.0239 0.6036 0.9517
1.000 0.3310 0.00933 0.00427 -0.0265 0.5917 0.9595
1.250 0.3759 0.00944 0.00434 -0.0301 0.5783 0.9625
1.500 0.4079 0.00947 0.00432 -0.0311 0.5654 0.9653
1.750 0.4345 0.00955 0.00436 -0.0310 0.5529 0.9692
2.000 0.4634 0.00959 0.00435 -0.0313 0.5401 0.9721
2.250 0.4974 0.00959 0.00429 -0.0328 0.5264 0.9736
2.500 0.5306 0.00961 0.00427 -0.0341 0.5131 0.9755
2.750 0.5617 0.00966 0.00427 -0.0350 0.5010 0.9778
3.000 0.5907 0.00973 0.00431 -0.0354 0.4891 0.9808
3.250 0.6177 0.00984 0.00440 -0.0354 0.4785 0.9839
3.500 0.6513 0.00983 0.00436 -0.0369 0.4673 0.9853
3.750 0.6836 0.00986 0.00435 -0.0381 0.4558 0.9870
4.000 0.7154 0.00989 0.00439 -0.0391 0.4458 0.9891
4.250 0.7459 0.00995 0.00445 -0.0399 0.4370 0.9915
4.500 0.7749 0.01007 0.00455 -0.0404 0.4266 0.9938
4.750 0.8071 0.01008 0.00455 -0.0416 0.4131 0.9955
5.000 0.8389 0.01010 0.00456 -0.0427 0.3948 0.9975
5.250 0.8708 0.01013 0.00458 -0.0439 0.3780 0.9994
5.500 0.8965 0.01023 0.00469 -0.0437 0.3627 1.0000
5.750 0.9177 0.01038 0.00482 -0.0426 0.3453 1.0000
6.000 0.9378 0.01060 0.00498 -0.0413 0.3202 1.0000
6.250 0.9568 0.01092 0.00518 -0.0399 0.2865 1.0000
6.500 0.9729 0.01147 0.00551 -0.0380 0.2393 1.0000
6.750 0.9850 0.01233 0.00604 -0.0355 0.1753 1.0000
7.000 0.9915 0.01362 0.00684 -0.0323 0.0937 1.0000
7.500 1.0105 0.01556 0.00840 -0.0262 0.0314 1.0000
7.750 1.0246 0.01611 0.00900 -0.0239 0.0279 1.0000
8.000 1.0340 0.01692 0.00986 -0.0208 0.0252 1.0000
8.250 1.0467 0.01745 0.01047 -0.0182 0.0238 1.0000
8.500 1.0585 0.01799 0.01107 -0.0155 0.0224 1.0000
8.750 1.0681 0.01860 0.01172 -0.0125 0.0212 1.0000
9.000 1.0732 0.01937 0.01253 -0.0087 0.0201 1.0000
9.250 1.0684 0.02051 0.01375 -0.0034 0.0190 1.0000
9.500 1.0695 0.02113 0.01444 0.0011 0.0187 1.0000
9.750 1.0659 0.02172 0.01509 0.0065 0.0184 1.0000
10.000 1.0631 0.02246 0.01591 0.0113 0.0180 1.0000
10.250 1.0619 0.02336 0.01688 0.0154 0.0175 1.0000
10.500 1.0625 0.02435 0.01795 0.0189 0.0171 1.0000
10.750 1.0642 0.02545 0.01910 0.0219 0.0164 1.0000
11.000 1.0662 0.02668 0.02038 0.0244 0.0160 1.0000
11.250 1.0680 0.02807 0.02181 0.0267 0.0156 1.0000
11.500 1.0646 0.03003 0.02382 0.0292 0.0150 1.0000
11.750 1.0620 0.03223 0.02608 0.0317 0.0147 1.0000
12.000 1.0699 0.03342 0.02738 0.0328 0.0143 1.0000
12.250 1.0751 0.03501 0.02907 0.0342 0.0140 1.0000
12.500 1.0797 0.03673 0.03089 0.0355 0.0136 1.0000
12.750 1.0846 0.03847 0.03273 0.0368 0.0134 1.0000
13.000 1.0892 0.04030 0.03464 0.0379 0.0131 1.0000
13.250 1.0935 0.04222 0.03666 0.0389 0.0129 1.0000
13.500 1.0973 0.04418 0.03872 0.0397 0.0127 1.0000
13.750 1.0999 0.04629 0.04091 0.0403 0.0123 1.0000
14.000 1.1025 0.04863 0.04338 0.0414 0.0123 1.0000
14.250 1.1034 0.05089 0.04569 0.0414 0.0120 1.0000
14.500 1.1038 0.05345 0.04838 0.0418 0.0119 1.0000
14.750 1.1035 0.05610 0.05109 0.0421 0.0115 1.0000
15.000 1.1005 0.05924 0.05440 0.0422 0.0116 1.0000
15.250 1.0975 0.06240 0.05765 0.0421 0.0114 1.0000
15.500 1.0831 0.06748 0.06294 0.0423 0.0111 1.0000
15.750 1.0747 0.07152 0.06713 0.0414 0.0111 1.0000
16.000 1.0613 0.07650 0.07229 0.0400 0.0111 1.0000
16.250 1.0505 0.08120 0.07713 0.0383 0.0111 1.0000
16.500 1.0289 0.08792 0.08406 0.0358 0.0111 1.0000
16.750 1.0210 0.09258 0.08883 0.0335 0.0111 1.0000
17.000 0.9971 0.10023 0.09667 0.0299 0.0111 1.0000
17.250 0.9810 0.10727 0.10390 0.0250 0.0108 1.0000
17.500 0.7540 0.11530 0.11257 0.0268 0.0129 1.0000
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