RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 100,000 Max Cl/Cd: 51.19 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf26-il-100000-n5.txt Download as CSV file: xf-raf26-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4844 0.09041 0.08545 -0.0229 1.0000 0.0250
-8.000 -0.4856 0.08688 0.08199 -0.0235 1.0000 0.0241
-7.750 -0.4889 0.08346 0.07864 -0.0244 1.0000 0.0234
-7.500 -0.4916 0.07967 0.07492 -0.0259 1.0000 0.0227
-7.250 -0.4915 0.07515 0.07046 -0.0289 1.0000 0.0220
-7.000 -0.4892 0.07025 0.06559 -0.0324 1.0000 0.0213
-6.750 -0.4849 0.06484 0.06015 -0.0361 1.0000 0.0206
-6.500 -0.4786 0.05898 0.05421 -0.0395 1.0000 0.0199
-6.250 -0.4705 0.05266 0.04770 -0.0424 1.0000 0.0190
-6.000 -0.4604 0.04613 0.04084 -0.0441 1.0000 0.0182
-5.750 -0.4478 0.04084 0.03513 -0.0445 1.0000 0.0177
-5.500 -0.4335 0.03654 0.03038 -0.0442 1.0000 0.0177
-5.250 -0.4179 0.03367 0.02719 -0.0437 1.0000 0.0188
-5.000 -0.4004 0.03124 0.02443 -0.0429 1.0000 0.0205
-4.750 -0.3813 0.02827 0.02094 -0.0418 1.0000 0.0215
-4.500 -0.3606 0.02544 0.01756 -0.0405 1.0000 0.0220
-4.250 -0.3388 0.02308 0.01471 -0.0392 1.0000 0.0229
-4.000 -0.3162 0.02117 0.01239 -0.0379 1.0000 0.0247
-3.750 -0.2940 0.01973 0.01065 -0.0367 1.0000 0.0281
-3.500 -0.2725 0.01855 0.00938 -0.0355 1.0000 0.0313
-3.250 -0.2506 0.01753 0.00818 -0.0342 1.0000 0.0369
-3.000 -0.2290 0.01675 0.00732 -0.0331 1.0000 0.0470
-2.750 -0.2073 0.01595 0.00657 -0.0321 1.0000 0.0691
-2.500 -0.1857 0.01524 0.00597 -0.0312 1.0000 0.1110
-2.250 -0.1590 0.01454 0.00553 -0.0314 0.9981 0.1857
-2.000 -0.1270 0.01370 0.00540 -0.0330 0.9936 0.3740
-1.750 -0.0951 0.01310 0.00534 -0.0341 0.9890 0.5424
-1.500 -0.0652 0.01250 0.00525 -0.0341 0.9844 0.7140
-1.250 -0.0078 0.01201 0.00499 -0.0399 0.9851 1.0000
-1.000 0.0292 0.01211 0.00484 -0.0421 0.9786 1.0000
-0.750 0.0647 0.01217 0.00471 -0.0440 0.9702 1.0000
-0.500 0.0999 0.01222 0.00461 -0.0458 0.9615 1.0000
-0.250 0.1367 0.01226 0.00451 -0.0478 0.9532 1.0000
0.000 0.1727 0.01228 0.00443 -0.0496 0.9444 1.0000
0.250 0.2072 0.01230 0.00439 -0.0511 0.9354 1.0000
0.500 0.2462 0.01228 0.00433 -0.0534 0.9288 1.0000
0.750 0.2804 0.01228 0.00431 -0.0548 0.9194 1.0000
1.000 0.3198 0.01223 0.00427 -0.0571 0.9108 1.0000
1.250 0.3621 0.01210 0.00418 -0.0598 0.8985 1.0000
1.500 0.4006 0.01201 0.00412 -0.0616 0.8830 1.0000
1.750 0.4362 0.01199 0.00416 -0.0629 0.8677 1.0000
2.000 0.4701 0.01198 0.00425 -0.0639 0.8504 1.0000
2.250 0.5038 0.01197 0.00430 -0.0646 0.8298 1.0000
2.500 0.5342 0.01199 0.00438 -0.0646 0.8032 1.0000
2.750 0.5618 0.01203 0.00450 -0.0640 0.7691 1.0000
3.000 0.5902 0.01211 0.00460 -0.0635 0.7323 1.0000
3.250 0.6167 0.01226 0.00474 -0.0625 0.6840 1.0000
3.500 0.6414 0.01253 0.00494 -0.0613 0.6240 1.0000
3.750 0.6613 0.01306 0.00514 -0.0591 0.5121 1.0000
4.000 0.6766 0.01403 0.00551 -0.0564 0.3960 1.0000
4.250 0.6899 0.01540 0.00614 -0.0539 0.2271 1.0000
4.500 0.7062 0.01673 0.00699 -0.0520 0.1377 1.0000
4.750 0.7227 0.01804 0.00787 -0.0504 0.0837 1.0000
5.000 0.7426 0.01901 0.00895 -0.0489 0.0529 1.0000
5.250 0.7621 0.02009 0.00996 -0.0472 0.0346 1.0000
5.500 0.7814 0.02119 0.01114 -0.0455 0.0272 1.0000
5.750 0.7993 0.02262 0.01270 -0.0436 0.0237 1.0000
6.000 0.8187 0.02431 0.01458 -0.0418 0.0219 1.0000
6.250 0.8401 0.02612 0.01658 -0.0404 0.0196 1.0000
6.500 0.8606 0.02800 0.01868 -0.0392 0.0170 1.0000
6.750 0.8809 0.03126 0.02227 -0.0379 0.0160 1.0000
7.000 0.8998 0.03450 0.02593 -0.0362 0.0157 1.0000
7.250 0.9158 0.03769 0.02963 -0.0342 0.0155 1.0000
7.500 0.9279 0.04120 0.03364 -0.0319 0.0154 1.0000
7.750 0.9359 0.04504 0.03798 -0.0293 0.0154 1.0000
8.000 0.9406 0.04895 0.04234 -0.0266 0.0153 1.0000
8.250 0.9423 0.05282 0.04659 -0.0241 0.0153 1.0000
8.500 0.9403 0.05679 0.05095 -0.0216 0.0151 1.0000
8.750 0.9343 0.06086 0.05531 -0.0192 0.0150 1.0000
9.000 0.9247 0.06482 0.05953 -0.0169 0.0148 1.0000
9.250 0.9098 0.06848 0.06336 -0.0146 0.0149 1.0000
9.500 0.8938 0.07227 0.06727 -0.0134 0.0152 1.0000
9.750 0.8764 0.07685 0.07198 -0.0141 0.0151 1.0000
10.000 0.8601 0.08210 0.07731 -0.0165 0.0153 1.0000
10.250 0.8455 0.08818 0.08344 -0.0202 0.0156 1.0000
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Polar data table (+)
Polar graphs
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