BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.89 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe103-il-1000000.txt Download as CSV file: xf-boe103-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 103 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7958 0.04995 0.04758 -0.0793 1.0000 0.0165
-13.250 -0.8356 0.04123 0.03861 -0.0864 1.0000 0.0165
-13.000 -0.8643 0.03763 0.03485 -0.0854 1.0000 0.0165
-12.750 -0.8952 0.03591 0.03303 -0.0792 1.0000 0.0166
-12.500 -0.9109 0.03429 0.03128 -0.0743 1.0000 0.0167
-12.250 -0.9095 0.03279 0.02962 -0.0721 0.9994 0.0168
-12.000 -0.8960 0.02904 0.02554 -0.0743 0.9966 0.0173
-11.750 -0.8654 0.02825 0.02472 -0.0761 0.9950 0.0176
-11.500 -0.8322 0.02786 0.02434 -0.0780 0.9940 0.0178
-11.250 -0.8026 0.02743 0.02388 -0.0791 0.9916 0.0181
-11.000 -0.7734 0.02680 0.02320 -0.0803 0.9891 0.0184
-10.750 -0.7445 0.02581 0.02211 -0.0817 0.9870 0.0188
-10.500 -0.7156 0.02453 0.02067 -0.0832 0.9852 0.0193
-10.250 -0.6857 0.02324 0.01919 -0.0847 0.9838 0.0199
-10.000 -0.6586 0.02244 0.01822 -0.0852 0.9803 0.0203
-9.750 -0.6340 0.02057 0.01612 -0.0859 0.9766 0.0209
-9.500 -0.6034 0.01961 0.01513 -0.0872 0.9745 0.0213
-9.250 -0.5713 0.01911 0.01461 -0.0885 0.9725 0.0218
-9.000 -0.5431 0.01857 0.01403 -0.0889 0.9683 0.0222
-8.750 -0.5162 0.01792 0.01331 -0.0890 0.9625 0.0227
-8.500 -0.4861 0.01718 0.01247 -0.0897 0.9586 0.0232
-8.250 -0.4604 0.01654 0.01173 -0.0895 0.9507 0.0237
-8.000 -0.4306 0.01608 0.01115 -0.0899 0.9447 0.0242
-7.750 -0.4027 0.01606 0.01103 -0.0898 0.9362 0.0246
-7.500 -0.3783 0.01423 0.00908 -0.0897 0.9282 0.0254
-7.250 -0.3526 0.01362 0.00844 -0.0894 0.9187 0.0258
-7.000 -0.3259 0.01316 0.00793 -0.0892 0.9102 0.0263
-6.750 -0.2997 0.01274 0.00744 -0.0888 0.9013 0.0268
-6.500 -0.2733 0.01237 0.00702 -0.0885 0.8929 0.0274
-6.250 -0.2468 0.01203 0.00661 -0.0882 0.8842 0.0280
-6.000 -0.2205 0.01166 0.00619 -0.0878 0.8762 0.0284
-5.750 -0.1940 0.01133 0.00579 -0.0874 0.8678 0.0288
-5.500 -0.1673 0.01106 0.00547 -0.0871 0.8597 0.0292
-5.250 -0.1404 0.01085 0.00520 -0.0867 0.8513 0.0295
-5.000 -0.1164 0.01008 0.00438 -0.0861 0.8430 0.0303
-4.750 -0.0905 0.00972 0.00398 -0.0856 0.8345 0.0310
-4.500 -0.0640 0.00944 0.00368 -0.0853 0.8259 0.0316
-4.250 -0.0375 0.00923 0.00340 -0.0849 0.8168 0.0322
-4.000 -0.0107 0.00901 0.00315 -0.0845 0.8066 0.0328
-3.750 0.0159 0.00883 0.00292 -0.0841 0.7957 0.0335
-3.250 0.0695 0.00854 0.00252 -0.0834 0.7723 0.0347
-3.000 0.0962 0.00838 0.00230 -0.0830 0.7604 0.0357
-2.750 0.1227 0.00823 0.00210 -0.0826 0.7472 0.0374
-2.500 0.1494 0.00813 0.00195 -0.0822 0.7343 0.0389
-2.250 0.1765 0.00805 0.00182 -0.0819 0.7217 0.0407
-2.000 0.2036 0.00796 0.00170 -0.0816 0.7099 0.0450
-1.750 0.2292 0.00766 0.00159 -0.0812 0.6987 0.1016
-1.500 0.2554 0.00750 0.00154 -0.0808 0.6872 0.1477
-1.250 0.2823 0.00737 0.00150 -0.0806 0.6756 0.1827
-1.000 0.3085 0.00719 0.00145 -0.0803 0.6647 0.2367
-0.750 0.3330 0.00680 0.00141 -0.0798 0.6544 0.3673
-0.500 0.3583 0.00649 0.00141 -0.0793 0.6434 0.4771
-0.250 0.3836 0.00630 0.00143 -0.0788 0.6308 0.5601
0.000 0.4086 0.00614 0.00146 -0.0782 0.6190 0.6450
0.250 0.4345 0.00605 0.00149 -0.0777 0.6087 0.7020
0.500 0.4596 0.00593 0.00154 -0.0770 0.5981 0.7649
0.750 0.4830 0.00580 0.00161 -0.0758 0.5864 0.8408
1.000 0.5056 0.00577 0.00171 -0.0743 0.5732 0.9101
1.250 0.5323 0.00585 0.00180 -0.0737 0.5591 0.9507
1.500 0.5654 0.00597 0.00187 -0.0746 0.5451 0.9713
1.750 0.5993 0.00611 0.00194 -0.0758 0.5292 0.9827
2.000 0.6387 0.00628 0.00201 -0.0784 0.5106 0.9882
2.250 0.6763 0.00645 0.00208 -0.0805 0.4905 0.9937
2.500 0.7186 0.00668 0.00217 -0.0838 0.4619 0.9978
2.750 0.7509 0.00696 0.00227 -0.0849 0.4268 1.0000
3.000 0.7708 0.00723 0.00239 -0.0834 0.3953 1.0000
3.250 0.7905 0.00752 0.00252 -0.0818 0.3669 1.0000
3.500 0.8111 0.00777 0.00266 -0.0804 0.3436 1.0000
3.750 0.8322 0.00801 0.00280 -0.0790 0.3246 1.0000
4.000 0.8543 0.00822 0.00293 -0.0779 0.3105 1.0000
4.250 0.8766 0.00842 0.00307 -0.0768 0.2982 1.0000
4.500 0.8992 0.00863 0.00321 -0.0757 0.2858 1.0000
4.750 0.9223 0.00883 0.00336 -0.0748 0.2730 1.0000
5.000 0.9457 0.00904 0.00351 -0.0740 0.2598 1.0000
5.250 0.9690 0.00929 0.00368 -0.0732 0.2449 1.0000
5.500 0.9918 0.00958 0.00388 -0.0723 0.2269 1.0000
5.750 1.0140 0.00992 0.00411 -0.0713 0.2052 1.0000
6.000 1.0349 0.01037 0.00440 -0.0701 0.1788 1.0000
6.250 1.0553 0.01085 0.00473 -0.0689 0.1531 1.0000
6.500 1.0762 0.01130 0.00506 -0.0678 0.1319 1.0000
6.750 1.0977 0.01172 0.00539 -0.0668 0.1173 1.0000
7.000 1.1200 0.01207 0.00569 -0.0659 0.1083 1.0000
7.250 1.1422 0.01243 0.00599 -0.0650 0.1018 1.0000
7.500 1.1650 0.01273 0.00628 -0.0643 0.0974 1.0000
7.750 1.1882 0.01300 0.00656 -0.0635 0.0949 1.0000
8.000 1.2104 0.01332 0.00687 -0.0627 0.0919 1.0000
8.250 1.2323 0.01366 0.00719 -0.0618 0.0890 1.0000
8.500 1.2535 0.01403 0.00756 -0.0608 0.0861 1.0000
8.750 1.2762 0.01426 0.00783 -0.0600 0.0851 1.0000
9.000 1.2974 0.01453 0.00812 -0.0590 0.0838 1.0000
9.250 1.3178 0.01484 0.00845 -0.0579 0.0821 1.0000
9.500 1.3372 0.01520 0.00880 -0.0566 0.0796 1.0000
9.750 1.3559 0.01561 0.00921 -0.0552 0.0769 1.0000
10.000 1.3744 0.01602 0.00964 -0.0539 0.0746 1.0000
10.250 1.3951 0.01631 0.00997 -0.0529 0.0734 1.0000
10.500 1.4148 0.01666 0.01035 -0.0518 0.0713 1.0000
10.750 1.4328 0.01710 0.01078 -0.0506 0.0680 1.0000
11.000 1.4496 0.01762 0.01129 -0.0491 0.0643 1.0000
11.250 1.4678 0.01807 0.01175 -0.0479 0.0603 1.0000
11.500 1.4807 0.01883 0.01243 -0.0461 0.0498 1.0000
11.750 1.4893 0.01987 0.01338 -0.0439 0.0401 1.0000
12.000 1.5002 0.02081 0.01431 -0.0420 0.0360 1.0000
12.250 1.5120 0.02171 0.01523 -0.0403 0.0329 1.0000
12.500 1.5218 0.02277 0.01631 -0.0385 0.0300 1.0000
12.750 1.5341 0.02369 0.01726 -0.0371 0.0272 1.0000
13.000 1.5405 0.02506 0.01861 -0.0353 0.0170 1.0000
13.250 1.5395 0.02707 0.02060 -0.0329 0.0131 1.0000
13.500 1.5453 0.02862 0.02222 -0.0313 0.0119 1.0000
13.750 1.5534 0.03003 0.02372 -0.0300 0.0114 1.0000
14.000 1.5603 0.03160 0.02537 -0.0288 0.0110 1.0000
14.250 1.5654 0.03336 0.02721 -0.0276 0.0107 1.0000
14.500 1.5685 0.03536 0.02930 -0.0265 0.0103 1.0000
14.750 1.5696 0.03762 0.03166 -0.0254 0.0100 1.0000
15.000 1.5683 0.04018 0.03432 -0.0244 0.0097 1.0000
15.250 1.5695 0.04261 0.03684 -0.0238 0.0095 1.0000
15.500 1.5718 0.04501 0.03933 -0.0234 0.0093 1.0000
15.750 1.5725 0.04764 0.04206 -0.0230 0.0092 1.0000
16.000 1.5716 0.05053 0.04505 -0.0228 0.0090 1.0000
16.250 1.5692 0.05371 0.04833 -0.0229 0.0088 1.0000
16.500 1.5652 0.05717 0.05189 -0.0230 0.0087 1.0000
16.750 1.5599 0.06087 0.05569 -0.0234 0.0086 1.0000
17.000 1.5531 0.06488 0.05981 -0.0240 0.0084 1.0000
17.250 1.5443 0.06926 0.06431 -0.0248 0.0083 1.0000
17.500 1.5339 0.07397 0.06913 -0.0258 0.0082 1.0000
17.750 1.5209 0.07916 0.07444 -0.0271 0.0081 1.0000
18.000 1.5063 0.08475 0.08015 -0.0287 0.0080 1.0000
18.250 1.4899 0.09075 0.08628 -0.0307 0.0080 1.0000
18.500 1.4712 0.09723 0.09289 -0.0329 0.0079 1.0000
18.750 1.4515 0.10403 0.09983 -0.0354 0.0079 1.0000
19.000 1.4313 0.11106 0.10699 -0.0382 0.0078 1.0000
19.250 1.4113 0.11813 0.11419 -0.0411 0.0078 1.0000
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Polar data table (+)
Polar graphs
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