TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 100,000 Max Cl/Cd: 49.65 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi12-il-100000-n5.txt Download as CSV file: xf-tsagi12-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5143 0.09187 0.08689 -0.0315 1.0000 0.0299
-10.500 -0.5275 0.08492 0.08001 -0.0354 1.0000 0.0298
-10.250 -0.6273 0.06105 0.05586 -0.0502 1.0000 0.0263
-10.000 -0.6494 0.05740 0.05206 -0.0481 1.0000 0.0263
-9.750 -0.6726 0.05412 0.04862 -0.0441 1.0000 0.0263
-9.500 -0.6902 0.05090 0.04521 -0.0401 1.0000 0.0265
-9.250 -0.6955 0.04863 0.04285 -0.0369 1.0000 0.0271
-9.000 -0.6956 0.04690 0.04102 -0.0340 1.0000 0.0278
-8.750 -0.6983 0.04465 0.03858 -0.0305 1.0000 0.0286
-8.500 -0.7004 0.04221 0.03590 -0.0268 1.0000 0.0293
-8.250 -0.7022 0.03955 0.03292 -0.0228 1.0000 0.0300
-8.000 -0.7017 0.03698 0.03000 -0.0188 1.0000 0.0309
-7.750 -0.6987 0.03475 0.02738 -0.0150 1.0000 0.0325
-7.500 -0.6942 0.03263 0.02477 -0.0111 1.0000 0.0344
-7.250 -0.6869 0.03095 0.02294 -0.0079 1.0000 0.0359
-7.000 -0.6783 0.02990 0.02181 -0.0049 1.0000 0.0374
-6.750 -0.6527 0.02844 0.02011 -0.0051 0.9945 0.0403
-6.500 -0.6189 0.02669 0.01789 -0.0066 0.9865 0.0448
-6.250 -0.5857 0.02547 0.01664 -0.0083 0.9778 0.0484
-6.000 -0.5510 0.02448 0.01537 -0.0099 0.9690 0.0543
-5.750 -0.5149 0.02329 0.01413 -0.0120 0.9619 0.0591
-5.500 -0.4811 0.02249 0.01314 -0.0134 0.9520 0.0662
-5.250 -0.4464 0.02133 0.01193 -0.0150 0.9435 0.0718
-5.000 -0.4112 0.02045 0.01093 -0.0166 0.9346 0.0800
-4.750 -0.3805 0.01955 0.01006 -0.0175 0.9233 0.0898
-4.500 -0.3489 0.01873 0.00921 -0.0184 0.9117 0.1007
-4.250 -0.3168 0.01806 0.00852 -0.0193 0.8991 0.1145
-4.000 -0.2853 0.01748 0.00795 -0.0200 0.8858 0.1356
-3.750 -0.2560 0.01689 0.00747 -0.0203 0.8722 0.1686
-3.500 -0.2291 0.01623 0.00703 -0.0202 0.8591 0.2239
-3.250 -0.2041 0.01557 0.00665 -0.0198 0.8460 0.2970
-3.000 -0.1818 0.01471 0.00632 -0.0188 0.8334 0.4231
-2.750 -0.1224 0.01361 0.00647 -0.0242 0.8256 0.7257
-2.500 -0.0481 0.01406 0.00687 -0.0319 0.8168 0.8259
-2.250 -0.0164 0.01439 0.00705 -0.0318 0.8040 0.8643
-2.000 0.0164 0.01475 0.00724 -0.0320 0.7917 0.8905
-1.750 0.0603 0.01516 0.00745 -0.0344 0.7802 0.9103
-1.500 0.1076 0.01552 0.00762 -0.0376 0.7687 0.9298
-1.250 0.1605 0.01588 0.00782 -0.0421 0.7561 0.9524
-1.000 0.2151 0.01592 0.00771 -0.0474 0.7435 0.9682
-0.750 0.2537 0.01585 0.00751 -0.0497 0.7311 0.9769
-0.500 0.2916 0.01572 0.00726 -0.0520 0.7186 0.9841
-0.250 0.3285 0.01554 0.00696 -0.0541 0.7066 0.9897
0.000 0.3613 0.01543 0.00676 -0.0554 0.6942 0.9946
0.250 0.3946 0.01526 0.00652 -0.0569 0.6818 0.9987
0.500 0.4196 0.01522 0.00642 -0.0566 0.6697 1.0000
0.750 0.4410 0.01524 0.00637 -0.0556 0.6584 1.0000
1.000 0.4625 0.01527 0.00633 -0.0545 0.6474 1.0000
1.250 0.4840 0.01531 0.00634 -0.0535 0.6355 1.0000
1.500 0.5055 0.01537 0.00637 -0.0524 0.6239 1.0000
1.750 0.5271 0.01543 0.00641 -0.0513 0.6130 1.0000
2.250 0.5704 0.01560 0.00654 -0.0492 0.5910 1.0000
2.500 0.5921 0.01570 0.00665 -0.0482 0.5802 1.0000
2.750 0.6139 0.01580 0.00674 -0.0471 0.5701 1.0000
3.000 0.6356 0.01592 0.00687 -0.0461 0.5596 1.0000
3.250 0.6573 0.01605 0.00704 -0.0450 0.5489 1.0000
3.500 0.6790 0.01619 0.00720 -0.0439 0.5392 1.0000
3.750 0.7007 0.01634 0.00737 -0.0428 0.5294 1.0000
4.000 0.7222 0.01650 0.00760 -0.0418 0.5192 1.0000
4.250 0.7437 0.01667 0.00781 -0.0406 0.5099 1.0000
4.500 0.7652 0.01685 0.00804 -0.0395 0.5002 1.0000
4.750 0.7863 0.01705 0.00832 -0.0383 0.4903 1.0000
5.000 0.8077 0.01726 0.00856 -0.0371 0.4811 1.0000
5.250 0.8286 0.01748 0.00889 -0.0359 0.4712 1.0000
5.500 0.8492 0.01773 0.00923 -0.0346 0.4610 1.0000
5.750 0.8695 0.01797 0.00953 -0.0333 0.4502 1.0000
6.000 0.8894 0.01822 0.00983 -0.0318 0.4384 1.0000
6.250 0.9083 0.01848 0.01020 -0.0302 0.4244 1.0000
6.500 0.9265 0.01876 0.01055 -0.0284 0.4094 1.0000
6.750 0.9441 0.01905 0.01092 -0.0266 0.3937 1.0000
7.000 0.9598 0.01933 0.01134 -0.0245 0.3718 1.0000
7.250 0.9721 0.01965 0.01164 -0.0218 0.3382 1.0000
7.500 0.9825 0.02013 0.01201 -0.0188 0.2944 1.0000
7.750 0.9905 0.02086 0.01257 -0.0157 0.2463 1.0000
8.000 0.9941 0.02195 0.01336 -0.0120 0.1919 1.0000
8.250 0.9942 0.02332 0.01441 -0.0080 0.1383 1.0000
8.500 0.9899 0.02494 0.01569 -0.0035 0.0941 1.0000
8.750 0.9860 0.02646 0.01703 0.0010 0.0687 1.0000
9.000 0.9834 0.02779 0.01830 0.0053 0.0549 1.0000
9.250 0.9777 0.02896 0.01949 0.0102 0.0481 1.0000
9.500 0.9702 0.03028 0.02080 0.0149 0.0439 1.0000
9.750 0.9661 0.03164 0.02226 0.0187 0.0400 1.0000
10.000 0.9615 0.03324 0.02391 0.0219 0.0373 1.0000
10.250 0.9549 0.03518 0.02588 0.0248 0.0351 1.0000
10.500 0.9531 0.03700 0.02785 0.0270 0.0337 1.0000
10.750 0.9514 0.03897 0.02994 0.0289 0.0324 1.0000
11.250 0.9491 0.04322 0.03439 0.0318 0.0293 1.0000
11.500 0.9475 0.04554 0.03674 0.0330 0.0280 1.0000
11.750 0.9485 0.04773 0.03899 0.0343 0.0267 1.0000
12.000 0.9536 0.04961 0.04101 0.0354 0.0257 1.0000
12.250 0.9594 0.05156 0.04309 0.0366 0.0248 1.0000
12.500 0.9656 0.05355 0.04520 0.0377 0.0239 1.0000
12.750 0.9712 0.05569 0.04747 0.0387 0.0230 1.0000
13.000 0.9754 0.05797 0.04986 0.0394 0.0223 1.0000
13.250 0.9775 0.06050 0.05249 0.0399 0.0214 1.0000
13.500 0.9790 0.06313 0.05518 0.0402 0.0207 1.0000
13.750 0.9802 0.06617 0.05830 0.0408 0.0199 1.0000
14.000 0.9764 0.06953 0.06189 0.0405 0.0196 1.0000
14.250 0.9721 0.07314 0.06572 0.0402 0.0194 1.0000
14.500 0.9651 0.07721 0.07006 0.0395 0.0193 1.0000
14.750 0.9561 0.08163 0.07469 0.0383 0.0192 1.0000
15.000 0.9440 0.08669 0.07996 0.0366 0.0191 1.0000
15.250 0.9295 0.09234 0.08584 0.0343 0.0190 1.0000
15.500 0.9141 0.09844 0.09213 0.0316 0.0190 1.0000
15.750 0.8973 0.10511 0.09899 0.0283 0.0190 1.0000
16.000 0.8820 0.11179 0.10582 0.0249 0.0192 1.0000
16.250 0.8604 0.12029 0.11446 0.0202 0.0192 1.0000
16.500 0.8399 0.12915 0.12345 0.0153 0.0194 1.0000
16.750 0.8212 0.13816 0.13256 0.0104 0.0196 1.0000
17.000 0.7997 0.14880 0.14327 0.0047 0.0198 1.0000
17.250 0.7832 0.15879 0.15328 -0.0003 0.0200 1.0000
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