RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 200,000 Max Cl/Cd: 62.14 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf26-il-200000-n5.txt Download as CSV file: xf-raf26-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 26 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4866 0.08436 0.08092 -0.0219 1.0000 0.0098
-7.750 -0.4910 0.08097 0.07758 -0.0227 1.0000 0.0097
-7.500 -0.4959 0.07740 0.07408 -0.0239 1.0000 0.0095
-7.250 -0.4959 0.07298 0.06970 -0.0270 1.0000 0.0093
-7.000 -0.4939 0.06805 0.06478 -0.0307 1.0000 0.0091
-6.750 -0.4893 0.06271 0.05942 -0.0346 1.0000 0.0089
-6.500 -0.4826 0.05700 0.05364 -0.0381 1.0000 0.0087
-6.250 -0.4743 0.05102 0.04752 -0.0408 1.0000 0.0087
-6.000 -0.4642 0.04532 0.04160 -0.0424 1.0000 0.0085
-5.750 -0.4528 0.03970 0.03568 -0.0429 1.0000 0.0083
-5.500 -0.4399 0.03450 0.03010 -0.0425 1.0000 0.0082
-5.250 -0.4255 0.02966 0.02477 -0.0414 1.0000 0.0082
-5.000 -0.4091 0.02540 0.01982 -0.0399 1.0000 0.0084
-4.750 -0.3797 0.02162 0.01533 -0.0405 0.9976 0.0089
-4.500 -0.3483 0.01881 0.01188 -0.0410 0.9951 0.0109
-4.250 -0.3171 0.01774 0.01058 -0.0420 0.9917 0.0148
-4.000 -0.2846 0.01688 0.00948 -0.0431 0.9883 0.0198
-3.750 -0.2543 0.01551 0.00793 -0.0439 0.9850 0.0245
-3.500 -0.2240 0.01458 0.00686 -0.0444 0.9806 0.0256
-3.250 -0.1918 0.01377 0.00591 -0.0454 0.9772 0.0256
-3.000 -0.1629 0.01315 0.00516 -0.0456 0.9711 0.0258
-2.750 -0.1303 0.01266 0.00453 -0.0467 0.9669 0.0266
-2.500 -0.1014 0.01227 0.00402 -0.0469 0.9600 0.0278
-2.250 -0.0678 0.01192 0.00350 -0.0480 0.9550 0.0309
-2.000 -0.0390 0.01138 0.00315 -0.0483 0.9470 0.0744
-1.750 -0.0062 0.01071 0.00288 -0.0497 0.9416 0.1811
-1.500 0.0214 0.01000 0.00276 -0.0500 0.9335 0.3393
-1.250 0.0533 0.00940 0.00267 -0.0511 0.9287 0.4809
-1.000 0.0782 0.00863 0.00265 -0.0503 0.9213 0.6796
-0.750 0.1536 0.00806 0.00266 -0.0603 0.9259 1.0000
-0.500 0.1912 0.00801 0.00251 -0.0624 0.9190 1.0000
-0.250 0.2315 0.00795 0.00236 -0.0651 0.9114 1.0000
0.000 0.2768 0.00784 0.00218 -0.0687 0.8982 1.0000
0.250 0.3200 0.00777 0.00202 -0.0719 0.8793 1.0000
0.500 0.3570 0.00778 0.00196 -0.0737 0.8615 1.0000
0.750 0.3870 0.00783 0.00196 -0.0741 0.8422 1.0000
1.000 0.4159 0.00790 0.00199 -0.0741 0.8196 1.0000
1.250 0.4426 0.00799 0.00201 -0.0736 0.7942 1.0000
1.500 0.4679 0.00810 0.00203 -0.0728 0.7637 1.0000
1.750 0.4924 0.00825 0.00206 -0.0718 0.7274 1.0000
2.000 0.5153 0.00847 0.00210 -0.0705 0.6836 1.0000
2.250 0.5377 0.00871 0.00227 -0.0692 0.6433 1.0000
2.500 0.5593 0.00900 0.00240 -0.0677 0.5966 1.0000
2.750 0.5792 0.00938 0.00255 -0.0659 0.5252 1.0000
3.000 0.5953 0.01003 0.00277 -0.0634 0.4342 1.0000
3.250 0.6133 0.01068 0.00310 -0.0615 0.3584 1.0000
3.500 0.6274 0.01180 0.00352 -0.0592 0.2050 1.0000
3.750 0.6466 0.01258 0.00398 -0.0578 0.1279 1.0000
4.000 0.6675 0.01319 0.00441 -0.0566 0.0960 1.0000
4.250 0.6896 0.01369 0.00491 -0.0555 0.0843 1.0000
4.500 0.7112 0.01424 0.00550 -0.0544 0.0756 1.0000
4.750 0.7345 0.01461 0.00608 -0.0536 0.0614 1.0000
5.000 0.7572 0.01507 0.00636 -0.0527 0.0257 1.0000
5.250 0.7752 0.01623 0.00751 -0.0507 0.0137 1.0000
5.500 0.7955 0.01713 0.00859 -0.0491 0.0115 1.0000
5.750 0.8148 0.01824 0.00986 -0.0473 0.0099 1.0000
6.000 0.8340 0.01935 0.01104 -0.0459 0.0075 1.0000
6.250 0.8545 0.02040 0.01223 -0.0445 0.0060 1.0000
6.500 0.8739 0.02195 0.01400 -0.0428 0.0055 1.0000
6.750 0.8937 0.02383 0.01613 -0.0412 0.0052 1.0000
7.000 0.9133 0.02601 0.01862 -0.0396 0.0050 1.0000
7.250 0.9314 0.02869 0.02171 -0.0377 0.0049 1.0000
7.500 0.9465 0.03186 0.02537 -0.0354 0.0049 1.0000
7.750 0.9571 0.03567 0.02971 -0.0326 0.0048 1.0000
8.000 0.9629 0.03999 0.03455 -0.0294 0.0048 1.0000
8.250 0.9640 0.04468 0.03970 -0.0262 0.0049 1.0000
8.500 0.9613 0.04959 0.04499 -0.0230 0.0050 1.0000
8.750 0.9554 0.05422 0.04993 -0.0200 0.0051 1.0000
9.000 0.9449 0.05878 0.05474 -0.0172 0.0051 1.0000
9.250 0.9298 0.06266 0.05880 -0.0143 0.0051 1.0000
9.500 0.9113 0.06674 0.06303 -0.0122 0.0052 1.0000
9.750 0.8943 0.07099 0.06741 -0.0122 0.0053 1.0000
10.000 0.8751 0.07674 0.07328 -0.0147 0.0053 1.0000
10.250 0.8579 0.08416 0.08077 -0.0199 0.0053 1.0000
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Polar data table (+)
Polar graphs
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