RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 100,000 Max Cl/Cd: 35.38 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil2-il-100000-n5.txt Download as CSV file: xf-amsoil2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7216 0.07300 0.06707 -0.0413 1.0000 0.0466
-10.750 -0.7589 0.06494 0.05879 -0.0459 1.0000 0.0465
-10.500 -0.7924 0.05919 0.05278 -0.0462 1.0000 0.0465
-10.250 -0.8232 0.05326 0.04637 -0.0449 1.0000 0.0469
-10.000 -0.8161 0.05126 0.04430 -0.0441 1.0000 0.0476
-9.750 -0.8042 0.04980 0.04281 -0.0434 1.0000 0.0484
-9.500 -0.7977 0.04744 0.04026 -0.0424 1.0000 0.0493
-9.250 -0.7932 0.04447 0.03698 -0.0411 1.0000 0.0502
-9.000 -0.7880 0.04128 0.03339 -0.0396 1.0000 0.0512
-8.750 -0.7813 0.03818 0.02981 -0.0379 1.0000 0.0524
-8.500 -0.7708 0.03591 0.02717 -0.0361 1.0000 0.0538
-8.250 -0.7552 0.03493 0.02618 -0.0348 1.0000 0.0549
-8.000 -0.7417 0.03378 0.02493 -0.0329 1.0000 0.0562
-7.750 -0.7292 0.03241 0.02336 -0.0309 1.0000 0.0575
-7.500 -0.7167 0.03093 0.02162 -0.0287 1.0000 0.0589
-7.250 -0.7036 0.02954 0.01989 -0.0266 1.0000 0.0607
-7.000 -0.6868 0.02876 0.01915 -0.0252 0.9994 0.0621
-6.750 -0.6546 0.02773 0.01803 -0.0268 0.9947 0.0644
-6.500 -0.6229 0.02650 0.01658 -0.0280 0.9900 0.0669
-6.250 -0.5902 0.02539 0.01534 -0.0294 0.9855 0.0696
-6.000 -0.5572 0.02461 0.01458 -0.0310 0.9813 0.0726
-5.750 -0.5252 0.02375 0.01359 -0.0321 0.9763 0.0761
-5.500 -0.4915 0.02287 0.01268 -0.0337 0.9725 0.0795
-5.250 -0.4585 0.02221 0.01205 -0.0351 0.9682 0.0839
-5.000 -0.4270 0.02154 0.01129 -0.0361 0.9631 0.0887
-4.750 -0.3945 0.02088 0.01072 -0.0374 0.9590 0.0938
-4.500 -0.3630 0.02035 0.01014 -0.0383 0.9542 0.1005
-4.250 -0.3341 0.01980 0.00969 -0.0389 0.9483 0.1071
-4.000 -0.3022 0.01929 0.00920 -0.0399 0.9439 0.1159
-3.750 -0.2732 0.01889 0.00882 -0.0404 0.9386 0.1263
-3.500 -0.2457 0.01846 0.00848 -0.0406 0.9326 0.1382
-3.250 -0.2152 0.01802 0.00813 -0.0413 0.9280 0.1547
-3.000 -0.1875 0.01763 0.00783 -0.0415 0.9224 0.1766
-2.750 -0.1613 0.01714 0.00756 -0.0415 0.9161 0.2122
-2.500 -0.1346 0.01624 0.00722 -0.0419 0.9114 0.3113
-2.250 -0.1173 0.01512 0.00737 -0.0399 0.9054 0.5773
-2.000 -0.0949 0.01511 0.00767 -0.0379 0.8989 0.6786
-1.750 -0.0688 0.01521 0.00786 -0.0367 0.8942 0.7320
-1.500 -0.0447 0.01538 0.00807 -0.0352 0.8887 0.7683
-1.250 -0.0219 0.01556 0.00828 -0.0335 0.8822 0.7955
-1.000 0.0033 0.01569 0.00840 -0.0322 0.8772 0.8202
-0.750 0.0282 0.01584 0.00856 -0.0306 0.8728 0.8419
-0.500 0.0491 0.01607 0.00882 -0.0284 0.8660 0.8639
-0.250 0.0740 0.01622 0.00898 -0.0268 0.8609 0.8855
0.000 0.1036 0.01627 0.00902 -0.0264 0.8570 0.9008
0.250 0.1293 0.01634 0.00909 -0.0261 0.8507 0.9109
0.500 0.1602 0.01637 0.00913 -0.0267 0.8452 0.9177
0.750 0.1896 0.01636 0.00911 -0.0269 0.8406 0.9264
1.000 0.2230 0.01636 0.00913 -0.0278 0.8348 0.9326
1.250 0.2523 0.01621 0.00899 -0.0277 0.8238 0.9408
1.500 0.2843 0.01591 0.00869 -0.0277 0.8087 0.9468
1.750 0.3154 0.01559 0.00835 -0.0275 0.7921 0.9539
2.000 0.3478 0.01529 0.00806 -0.0277 0.7745 0.9604
2.250 0.3803 0.01500 0.00777 -0.0279 0.7540 0.9672
2.500 0.4135 0.01470 0.00744 -0.0282 0.7301 0.9735
2.750 0.4467 0.01450 0.00723 -0.0288 0.6961 0.9805
3.000 0.4803 0.01433 0.00696 -0.0294 0.6435 0.9870
3.250 0.5105 0.01443 0.00657 -0.0292 0.5229 0.9943
3.500 0.5243 0.01611 0.00682 -0.0274 0.2736 1.0000
3.750 0.5356 0.01698 0.00725 -0.0250 0.2072 1.0000
4.000 0.5497 0.01757 0.00763 -0.0230 0.1770 1.0000
4.250 0.5660 0.01811 0.00803 -0.0212 0.1574 1.0000
4.500 0.5842 0.01866 0.00845 -0.0198 0.1428 1.0000
4.750 0.6045 0.01919 0.00892 -0.0187 0.1310 1.0000
5.000 0.6255 0.01975 0.00943 -0.0177 0.1214 1.0000
5.250 0.6463 0.02041 0.00997 -0.0168 0.1138 1.0000
5.500 0.6689 0.02097 0.01055 -0.0160 0.1066 1.0000
5.750 0.6904 0.02168 0.01116 -0.0152 0.1012 1.0000
6.000 0.7136 0.02233 0.01184 -0.0146 0.0957 1.0000
6.250 0.7363 0.02303 0.01249 -0.0139 0.0911 1.0000
6.500 0.7593 0.02385 0.01328 -0.0133 0.0873 1.0000
6.750 0.7831 0.02461 0.01409 -0.0128 0.0831 1.0000
7.000 0.8063 0.02542 0.01483 -0.0123 0.0797 1.0000
7.250 0.8303 0.02638 0.01582 -0.0119 0.0768 1.0000
7.500 0.8545 0.02730 0.01685 -0.0114 0.0736 1.0000
7.750 0.8778 0.02819 0.01772 -0.0110 0.0709 1.0000
8.000 0.9015 0.02927 0.01876 -0.0106 0.0687 1.0000
8.250 0.9254 0.03049 0.02020 -0.0101 0.0662 1.0000
8.500 0.9481 0.03159 0.02142 -0.0096 0.0638 1.0000
8.750 0.9701 0.03261 0.02244 -0.0091 0.0618 1.0000
9.000 0.9920 0.03400 0.02392 -0.0086 0.0602 1.0000
9.250 1.0121 0.03569 0.02593 -0.0078 0.0582 1.0000
9.500 1.0312 0.03717 0.02760 -0.0069 0.0563 1.0000
9.750 1.0499 0.03840 0.02892 -0.0061 0.0548 1.0000
10.000 1.0690 0.03966 0.03017 -0.0055 0.0536 1.0000
10.250 1.0803 0.04217 0.03315 -0.0039 0.0523 1.0000
10.500 1.0889 0.04471 0.03607 -0.0021 0.0509 1.0000
10.750 1.0969 0.04690 0.03854 -0.0005 0.0497 1.0000
11.000 1.1055 0.04872 0.04052 0.0011 0.0486 1.0000
11.250 1.1144 0.05031 0.04222 0.0025 0.0478 1.0000
11.500 1.1244 0.05187 0.04381 0.0038 0.0471 1.0000
11.750 1.1078 0.05539 0.04775 0.0072 0.0466 1.0000
12.000 1.0864 0.05949 0.05224 0.0099 0.0462 1.0000
12.250 1.0613 0.06419 0.05729 0.0114 0.0459 1.0000
12.500 1.0318 0.06979 0.06321 0.0115 0.0458 1.0000
12.750 0.9969 0.07679 0.07050 0.0097 0.0458 1.0000
13.000 0.9535 0.08637 0.08034 0.0048 0.0461 1.0000
13.250 0.8893 0.10359 0.09782 -0.0070 0.0466 1.0000
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