RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 500,000 Max Cl/Cd: 93.33 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf31-il-500000.txt Download as CSV file: xf-raf31-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8248 0.05594 0.05256 -0.0747 1.0000 0.0239
-13.250 -0.8385 0.05154 0.04806 -0.0770 1.0000 0.0241
-13.000 -0.8602 0.04694 0.04326 -0.0789 1.0000 0.0240
-12.750 -0.8718 0.04387 0.04008 -0.0790 1.0000 0.0242
-12.500 -0.8785 0.04170 0.03784 -0.0780 1.0000 0.0245
-12.250 -0.8877 0.03981 0.03586 -0.0758 1.0000 0.0247
-12.000 -0.8882 0.03876 0.03480 -0.0731 1.0000 0.0250
-11.750 -0.8983 0.03742 0.03337 -0.0688 1.0000 0.0252
-11.500 -0.8955 0.03643 0.03234 -0.0661 1.0000 0.0257
-11.250 -0.8968 0.03515 0.03096 -0.0628 1.0000 0.0262
-11.000 -0.9004 0.03370 0.02937 -0.0590 1.0000 0.0266
-10.750 -0.9068 0.03261 0.02815 -0.0544 1.0000 0.0269
-10.500 -0.8930 0.03096 0.02626 -0.0537 0.9981 0.0275
-10.250 -0.8655 0.02932 0.02434 -0.0555 0.9949 0.0281
-10.000 -0.8375 0.02850 0.02325 -0.0568 0.9912 0.0286
-9.750 -0.8165 0.02476 0.01931 -0.0578 0.9877 0.0296
-9.500 -0.7865 0.02346 0.01797 -0.0593 0.9851 0.0305
-9.250 -0.7561 0.02231 0.01673 -0.0607 0.9824 0.0312
-9.000 -0.7290 0.02126 0.01558 -0.0612 0.9774 0.0320
-8.750 -0.6980 0.02019 0.01440 -0.0625 0.9742 0.0326
-8.500 -0.6649 0.01933 0.01344 -0.0641 0.9719 0.0335
-8.250 -0.6376 0.01860 0.01261 -0.0644 0.9665 0.0342
-8.000 -0.6065 0.01784 0.01176 -0.0653 0.9627 0.0346
-7.750 -0.5755 0.01655 0.01039 -0.0665 0.9599 0.0352
-7.500 -0.5463 0.01538 0.00917 -0.0674 0.9555 0.0361
-7.250 -0.5152 0.01459 0.00836 -0.0685 0.9499 0.0372
-7.000 -0.4799 0.01388 0.00761 -0.0704 0.9461 0.0381
-6.750 -0.4472 0.01328 0.00696 -0.0717 0.9405 0.0390
-6.500 -0.4147 0.01274 0.00636 -0.0729 0.9345 0.0399
-6.250 -0.3790 0.01223 0.00577 -0.0747 0.9295 0.0409
-6.000 -0.3511 0.01189 0.00536 -0.0748 0.9210 0.0417
-5.750 -0.3200 0.01139 0.00479 -0.0757 0.9143 0.0440
-5.500 -0.2954 0.01109 0.00446 -0.0750 0.9051 0.0459
-5.250 -0.2667 0.01083 0.00415 -0.0752 0.8979 0.0485
-5.000 -0.2430 0.01058 0.00390 -0.0743 0.8889 0.0539
-4.750 -0.2169 0.01028 0.00368 -0.0740 0.8818 0.0736
-4.500 -0.1934 0.01002 0.00347 -0.0731 0.8734 0.0931
-4.250 -0.1677 0.00976 0.00325 -0.0727 0.8666 0.1140
-4.000 -0.1455 0.00939 0.00304 -0.0716 0.8577 0.1512
-3.750 -0.1215 0.00902 0.00285 -0.0709 0.8503 0.2056
-3.500 -0.0985 0.00872 0.00269 -0.0700 0.8415 0.2481
-3.250 -0.0741 0.00843 0.00255 -0.0694 0.8342 0.2985
-3.000 -0.0500 0.00823 0.00246 -0.0686 0.8255 0.3396
-2.750 -0.0246 0.00806 0.00236 -0.0680 0.8177 0.3748
-2.500 0.0003 0.00791 0.00227 -0.0673 0.8088 0.4048
-2.250 0.0257 0.00777 0.00219 -0.0667 0.8010 0.4332
-2.000 0.0506 0.00762 0.00212 -0.0660 0.7923 0.4632
-1.750 0.0758 0.00749 0.00206 -0.0654 0.7846 0.4948
-1.500 0.1008 0.00738 0.00203 -0.0647 0.7765 0.5298
-1.250 0.1258 0.00728 0.00202 -0.0640 0.7693 0.5683
-1.000 0.1512 0.00721 0.00200 -0.0634 0.7618 0.5963
-0.750 0.1770 0.00715 0.00199 -0.0628 0.7552 0.6226
-0.500 0.2025 0.00710 0.00199 -0.0621 0.7477 0.6484
-0.250 0.2283 0.00707 0.00199 -0.0615 0.7412 0.6727
0.000 0.2537 0.00702 0.00202 -0.0609 0.7337 0.6948
0.250 0.2795 0.00701 0.00203 -0.0603 0.7268 0.7179
0.500 0.3043 0.00697 0.00207 -0.0595 0.7192 0.7460
0.750 0.3291 0.00694 0.00211 -0.0586 0.7114 0.7752
1.000 0.3538 0.00690 0.00215 -0.0577 0.7031 0.8005
1.250 0.3791 0.00689 0.00217 -0.0569 0.6948 0.8251
1.500 0.4045 0.00684 0.00221 -0.0562 0.6859 0.8501
2.000 0.4650 0.00681 0.00232 -0.0568 0.6682 0.9048
2.250 0.5078 0.00687 0.00241 -0.0599 0.6562 0.9280
2.500 0.5531 0.00697 0.00247 -0.0636 0.6386 0.9456
2.750 0.5945 0.00708 0.00254 -0.0665 0.6190 0.9596
3.000 0.6303 0.00724 0.00262 -0.0681 0.5962 0.9735
3.250 0.6659 0.00743 0.00271 -0.0698 0.5670 0.9856
3.500 0.7033 0.00766 0.00281 -0.0720 0.5342 0.9944
3.750 0.7401 0.00793 0.00293 -0.0741 0.4985 1.0000
4.000 0.7560 0.00819 0.00305 -0.0718 0.4735 1.0000
4.250 0.7744 0.00842 0.00319 -0.0699 0.4552 1.0000
4.500 0.7934 0.00866 0.00336 -0.0681 0.4381 1.0000
4.750 0.8130 0.00889 0.00353 -0.0665 0.4224 1.0000
5.000 0.8330 0.00911 0.00371 -0.0649 0.4068 1.0000
5.250 0.8530 0.00934 0.00389 -0.0633 0.3877 1.0000
5.500 0.8722 0.00961 0.00408 -0.0616 0.3608 1.0000
5.750 0.8866 0.01009 0.00431 -0.0591 0.3020 1.0000
6.000 0.8991 0.01072 0.00469 -0.0562 0.2633 1.0000
6.250 0.9150 0.01120 0.00506 -0.0540 0.2357 1.0000
6.500 0.9256 0.01199 0.00548 -0.0509 0.1670 1.0000
6.750 0.9370 0.01272 0.00599 -0.0480 0.1315 1.0000
7.000 0.9526 0.01323 0.00641 -0.0458 0.1167 1.0000
7.250 0.9693 0.01366 0.00682 -0.0438 0.1070 1.0000
7.500 0.9849 0.01415 0.00725 -0.0416 0.0984 1.0000
7.750 1.0032 0.01448 0.00761 -0.0399 0.0932 1.0000
8.000 1.0190 0.01489 0.00800 -0.0377 0.0880 1.0000
8.250 1.0323 0.01534 0.00845 -0.0351 0.0834 1.0000
8.500 1.0498 0.01562 0.00878 -0.0333 0.0795 1.0000
8.750 1.0648 0.01603 0.00919 -0.0311 0.0756 1.0000
9.000 1.0778 0.01657 0.00972 -0.0287 0.0716 1.0000
9.250 1.0968 0.01684 0.01005 -0.0272 0.0682 1.0000
9.500 1.1129 0.01727 0.01048 -0.0254 0.0640 1.0000
9.750 1.1286 0.01773 0.01096 -0.0236 0.0593 1.0000
10.000 1.1452 0.01817 0.01140 -0.0220 0.0533 1.0000
10.250 1.1602 0.01872 0.01192 -0.0202 0.0446 1.0000
10.500 1.1711 0.01952 0.01265 -0.0180 0.0343 1.0000
10.750 1.1811 0.02041 0.01350 -0.0157 0.0285 1.0000
11.000 1.1908 0.02136 0.01445 -0.0136 0.0254 1.0000
11.250 1.1998 0.02239 0.01553 -0.0114 0.0237 1.0000
11.500 1.2107 0.02332 0.01653 -0.0096 0.0226 1.0000
11.750 1.2196 0.02442 0.01768 -0.0078 0.0215 1.0000
12.000 1.2238 0.02591 0.01920 -0.0056 0.0203 1.0000
12.250 1.2295 0.02733 0.02071 -0.0037 0.0197 1.0000
12.500 1.2378 0.02862 0.02209 -0.0022 0.0192 1.0000
12.750 1.2447 0.03008 0.02363 -0.0008 0.0186 1.0000
13.000 1.2510 0.03161 0.02524 0.0005 0.0180 1.0000
13.250 1.2554 0.03336 0.02706 0.0018 0.0175 1.0000
13.500 1.2589 0.03524 0.02902 0.0030 0.0172 1.0000
13.750 1.2575 0.03763 0.03145 0.0042 0.0166 1.0000
14.000 1.2555 0.04017 0.03408 0.0053 0.0161 1.0000
14.250 1.2585 0.04230 0.03632 0.0060 0.0159 1.0000
14.500 1.2615 0.04450 0.03863 0.0066 0.0156 1.0000
14.750 1.2635 0.04685 0.04107 0.0071 0.0155 1.0000
15.000 1.2653 0.04932 0.04366 0.0074 0.0150 1.0000
15.250 1.2652 0.05204 0.04647 0.0076 0.0149 1.0000
15.500 1.2651 0.05483 0.04937 0.0077 0.0147 1.0000
15.750 1.2639 0.05787 0.05250 0.0076 0.0144 1.0000
16.000 1.2628 0.06094 0.05567 0.0073 0.0143 1.0000
16.250 1.2606 0.06425 0.05906 0.0068 0.0140 1.0000
16.500 1.2581 0.06766 0.06256 0.0063 0.0139 1.0000
16.750 1.2537 0.07136 0.06633 0.0056 0.0136 1.0000
17.000 1.2503 0.07502 0.07011 0.0048 0.0135 1.0000
17.250 1.2448 0.07896 0.07413 0.0040 0.0134 1.0000
17.500 1.2389 0.08306 0.07834 0.0031 0.0133 1.0000
17.750 1.2285 0.08772 0.08313 0.0021 0.0131 1.0000
18.000 1.2202 0.09254 0.08809 0.0003 0.0130 1.0000
18.250 1.2115 0.09768 0.09337 -0.0020 0.0130 1.0000
18.500 1.2028 0.10280 0.09863 -0.0042 0.0129 1.0000
18.750 1.1899 0.10893 0.10493 -0.0073 0.0128 1.0000
19.000 1.1795 0.11469 0.11082 -0.0102 0.0128 1.0000
19.250 1.1656 0.12115 0.11743 -0.0135 0.0128 1.0000
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Polar data table (+)
Polar graphs
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