TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.65 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi12-il-1000000.txt Download as CSV file: xf-tsagi12-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7414 0.11234 0.11057 -0.0144 1.0000 0.0090
-15.000 -0.7688 0.10235 0.10054 -0.0192 1.0000 0.0087
-14.750 -0.9639 0.05614 0.05383 -0.0493 1.0000 0.0080
-14.500 -0.9611 0.05197 0.04959 -0.0530 1.0000 0.0082
-14.250 -1.0093 0.04234 0.03964 -0.0583 1.0000 0.0080
-14.000 -1.0183 0.03924 0.03640 -0.0581 1.0000 0.0081
-13.750 -1.0297 0.03633 0.03330 -0.0566 1.0000 0.0081
-13.500 -1.0325 0.03438 0.03121 -0.0547 1.0000 0.0083
-13.250 -1.0416 0.03209 0.02875 -0.0516 1.0000 0.0083
-13.000 -1.0447 0.03039 0.02689 -0.0485 1.0000 0.0084
-12.750 -1.0419 0.02916 0.02553 -0.0455 1.0000 0.0085
-12.500 -1.0407 0.02788 0.02411 -0.0421 1.0000 0.0085
-12.250 -1.0377 0.02680 0.02290 -0.0385 1.0000 0.0086
-12.000 -1.0359 0.02574 0.02170 -0.0345 1.0000 0.0086
-11.750 -1.0502 0.02318 0.01886 -0.0282 1.0000 0.0091
-11.500 -1.0423 0.02212 0.01770 -0.0251 1.0000 0.0093
-11.250 -1.0308 0.02133 0.01682 -0.0225 1.0000 0.0094
-11.000 -1.0162 0.02080 0.01624 -0.0203 1.0000 0.0098
-10.750 -1.0040 0.02003 0.01538 -0.0176 1.0000 0.0099
-10.500 -0.9884 0.01959 0.01489 -0.0154 1.0000 0.0104
-10.250 -0.9748 0.01897 0.01418 -0.0129 1.0000 0.0106
-10.000 -0.9600 0.01850 0.01364 -0.0105 1.0000 0.0109
-9.750 -0.9474 0.01788 0.01293 -0.0077 1.0000 0.0112
-9.500 -0.9320 0.01760 0.01260 -0.0054 1.0000 0.0114
-9.250 -0.9051 0.01632 0.01117 -0.0058 0.9980 0.0119
-9.000 -0.8727 0.01560 0.01041 -0.0073 0.9953 0.0128
-8.750 -0.8403 0.01512 0.00990 -0.0086 0.9919 0.0135
-8.500 -0.8083 0.01459 0.00931 -0.0097 0.9878 0.0141
-8.250 -0.7741 0.01418 0.00885 -0.0113 0.9844 0.0148
-8.000 -0.7456 0.01335 0.00794 -0.0117 0.9782 0.0157
-7.750 -0.7121 0.01284 0.00741 -0.0132 0.9723 0.0168
-7.500 -0.6740 0.01246 0.00702 -0.0156 0.9659 0.0180
-7.250 -0.6321 0.01220 0.00672 -0.0188 0.9568 0.0192
-7.000 -0.5928 0.01141 0.00585 -0.0216 0.9403 0.0211
-6.750 -0.5585 0.01113 0.00551 -0.0231 0.9142 0.0229
-6.500 -0.5318 0.01095 0.00521 -0.0228 0.8863 0.0242
-6.250 -0.5094 0.01069 0.00482 -0.0216 0.8621 0.0257
-6.000 -0.4877 0.01038 0.00443 -0.0203 0.8423 0.0280
-5.750 -0.4647 0.01021 0.00418 -0.0193 0.8248 0.0297
-5.500 -0.4410 0.01007 0.00395 -0.0184 0.8097 0.0312
-5.250 -0.4184 0.00980 0.00360 -0.0172 0.7952 0.0337
-5.000 -0.3952 0.00959 0.00334 -0.0163 0.7814 0.0366
-4.750 -0.3713 0.00943 0.00312 -0.0154 0.7689 0.0392
-4.500 -0.3477 0.00924 0.00289 -0.0145 0.7567 0.0442
-4.250 -0.3238 0.00904 0.00272 -0.0136 0.7446 0.0540
-4.000 -0.2994 0.00889 0.00258 -0.0129 0.7328 0.0657
-3.750 -0.2743 0.00882 0.00247 -0.0123 0.7216 0.0733
-3.500 -0.2499 0.00870 0.00231 -0.0115 0.7111 0.0801
-3.250 -0.2249 0.00857 0.00217 -0.0109 0.7009 0.0862
-3.000 -0.1999 0.00847 0.00204 -0.0103 0.6914 0.0925
-2.750 -0.1755 0.00835 0.00191 -0.0096 0.6816 0.1021
-2.500 -0.1519 0.00811 0.00179 -0.0087 0.6724 0.1377
-2.250 -0.1287 0.00789 0.00169 -0.0078 0.6641 0.1795
-2.000 -0.1053 0.00767 0.00160 -0.0069 0.6558 0.2239
-1.750 -0.0831 0.00739 0.00151 -0.0058 0.6479 0.2850
-1.500 -0.0634 0.00698 0.00140 -0.0043 0.6395 0.3796
-1.250 -0.0482 0.00640 0.00129 -0.0018 0.6321 0.5192
-1.000 -0.0420 0.00570 0.00118 0.0029 0.6246 0.6914
-0.750 -0.0319 0.00524 0.00118 0.0070 0.6175 0.8159
-0.500 -0.0048 0.00517 0.00122 0.0074 0.6089 0.8654
-0.250 0.0260 0.00518 0.00125 0.0069 0.6007 0.8880
0.000 0.0587 0.00524 0.00129 0.0059 0.5917 0.9032
0.250 0.0906 0.00530 0.00133 0.0051 0.5824 0.9157
0.500 0.1279 0.00543 0.00143 0.0031 0.5722 0.9268
0.750 0.1644 0.00557 0.00151 0.0012 0.5610 0.9332
1.000 0.1988 0.00572 0.00163 -0.0002 0.5490 0.9397
1.250 0.2288 0.00589 0.00175 -0.0005 0.5364 0.9456
1.500 0.2778 0.00627 0.00206 -0.0050 0.5208 0.9488
1.750 0.3219 0.00666 0.00238 -0.0083 0.5056 0.9531
2.000 0.3461 0.00683 0.00250 -0.0074 0.4920 0.9585
2.250 0.3855 0.00704 0.00264 -0.0100 0.4780 0.9594
2.500 0.4223 0.00721 0.00276 -0.0120 0.4657 0.9604
2.750 0.4545 0.00734 0.00284 -0.0131 0.4549 0.9614
3.000 0.4863 0.00745 0.00292 -0.0141 0.4446 0.9626
3.250 0.5172 0.00757 0.00300 -0.0148 0.4336 0.9641
3.500 0.5466 0.00768 0.00308 -0.0153 0.4253 0.9660
3.750 0.5711 0.00778 0.00318 -0.0146 0.4180 0.9693
4.000 0.5963 0.00790 0.00327 -0.0142 0.4106 0.9718
4.250 0.6298 0.00797 0.00335 -0.0155 0.4025 0.9725
4.500 0.6627 0.00808 0.00345 -0.0168 0.3937 0.9733
4.750 0.6952 0.00821 0.00354 -0.0180 0.3808 0.9743
5.000 0.7272 0.00834 0.00363 -0.0191 0.3653 0.9755
5.250 0.7580 0.00848 0.00374 -0.0200 0.3494 0.9769
5.500 0.7871 0.00864 0.00386 -0.0205 0.3328 0.9786
5.750 0.8129 0.00887 0.00401 -0.0203 0.3100 0.9810
6.000 0.8341 0.00921 0.00423 -0.0191 0.2798 0.9839
6.250 0.8629 0.00964 0.00446 -0.0199 0.2346 0.9847
6.500 0.8896 0.01030 0.00483 -0.0204 0.1771 0.9858
6.750 0.9130 0.01125 0.00538 -0.0204 0.1050 0.9875
7.000 0.9363 0.01206 0.00595 -0.0202 0.0586 0.9894
7.250 0.9589 0.01283 0.00653 -0.0198 0.0287 0.9916
7.500 0.9836 0.01330 0.00699 -0.0196 0.0229 0.9936
7.750 1.0105 0.01380 0.00750 -0.0199 0.0190 0.9949
8.000 1.0394 0.01414 0.00788 -0.0207 0.0177 0.9959
8.250 1.0670 0.01456 0.00831 -0.0212 0.0161 0.9972
8.500 1.0922 0.01523 0.00904 -0.0213 0.0145 0.9987
8.750 1.1202 0.01566 0.00952 -0.0219 0.0140 0.9999
9.000 1.1365 0.01606 0.00995 -0.0201 0.0133 1.0000
9.250 1.1498 0.01648 0.01041 -0.0177 0.0125 1.0000
9.500 1.1605 0.01700 0.01097 -0.0148 0.0121 1.0000
9.750 1.1671 0.01768 0.01169 -0.0113 0.0116 1.0000
10.000 1.1640 0.01869 0.01280 -0.0061 0.0111 1.0000
10.250 1.1717 0.01912 0.01329 -0.0027 0.0109 1.0000
10.500 1.1701 0.01953 0.01374 0.0024 0.0107 1.0000
10.750 1.1693 0.02000 0.01427 0.0072 0.0104 1.0000
11.000 1.1686 0.02067 0.01500 0.0116 0.0102 1.0000
11.250 1.1688 0.02148 0.01588 0.0155 0.0101 1.0000
11.500 1.1716 0.02234 0.01680 0.0187 0.0097 1.0000
11.750 1.1718 0.02348 0.01801 0.0217 0.0096 1.0000
12.000 1.1795 0.02433 0.01890 0.0237 0.0092 1.0000
12.250 1.1816 0.02566 0.02028 0.0259 0.0090 1.0000
12.500 1.1803 0.02737 0.02206 0.0281 0.0087 1.0000
12.750 1.1798 0.02920 0.02396 0.0298 0.0086 1.0000
13.000 1.1743 0.03158 0.02643 0.0315 0.0084 1.0000
13.250 1.1680 0.03420 0.02915 0.0330 0.0083 1.0000
13.500 1.1628 0.03684 0.03189 0.0341 0.0082 1.0000
13.750 1.1701 0.03845 0.03359 0.0345 0.0080 1.0000
14.000 1.1650 0.04125 0.03648 0.0354 0.0080 1.0000
14.250 1.1731 0.04290 0.03820 0.0355 0.0078 1.0000
14.500 1.1755 0.04513 0.04051 0.0356 0.0077 1.0000
14.750 1.1771 0.04753 0.04299 0.0357 0.0074 1.0000
15.000 1.1739 0.05043 0.04599 0.0359 0.0075 1.0000
15.250 1.1749 0.05304 0.04868 0.0356 0.0073 1.0000
15.500 1.1732 0.05607 0.05180 0.0352 0.0070 1.0000
15.750 1.1715 0.05913 0.05494 0.0348 0.0070 1.0000
16.000 1.1683 0.06249 0.05839 0.0342 0.0069 1.0000
16.250 1.1651 0.06592 0.06190 0.0334 0.0068 1.0000
16.500 1.1628 0.06938 0.06544 0.0324 0.0067 1.0000
16.750 1.1566 0.07333 0.06950 0.0315 0.0067 1.0000
17.000 1.1535 0.07708 0.07333 0.0302 0.0066 1.0000
17.250 1.1514 0.08083 0.07712 0.0286 0.0063 1.0000
17.500 1.1425 0.08538 0.08179 0.0273 0.0064 1.0000
17.750 1.1307 0.09040 0.08696 0.0259 0.0065 1.0000
18.000 1.1254 0.09481 0.09142 0.0240 0.0063 1.0000
18.250 1.1164 0.09976 0.09645 0.0221 0.0062 1.0000
18.500 1.1096 0.10448 0.10126 0.0201 0.0063 1.0000
18.750 1.0937 0.11069 0.10758 0.0175 0.0061 1.0000
19.000 1.0858 0.11588 0.11289 0.0152 0.0062 1.0000
19.250 1.0751 0.12163 0.11875 0.0126 0.0062 1.0000
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