RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 200,000 Max Cl/Cd: 67.54 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf34-il-200000.txt Download as CSV file: xf-raf34-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 34 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5581 0.09070 0.08712 -0.0387 1.0000 0.0817
-10.250 -0.5209 0.09001 0.08647 -0.0300 1.0000 0.0833
-10.000 -0.5055 0.08839 0.08484 -0.0279 1.0000 0.0846
-9.750 -0.5018 0.08519 0.08166 -0.0285 1.0000 0.0860
-9.500 -0.4903 0.06852 0.06522 -0.0420 1.0000 0.0943
-9.250 -0.5368 0.06403 0.06064 -0.0417 1.0000 0.0945
-9.000 -0.5736 0.06064 0.05710 -0.0388 1.0000 0.0948
-8.750 -0.5746 0.05312 0.04964 -0.0390 1.0000 0.0962
-8.500 -0.6982 0.04384 0.03890 -0.0299 1.0000 0.0579
-8.250 -0.6978 0.04039 0.03524 -0.0269 1.0000 0.0572
-8.000 -0.6983 0.03745 0.03205 -0.0232 1.0000 0.0569
-7.750 -0.7067 0.03549 0.02991 -0.0180 1.0000 0.0566
-7.500 -0.6804 0.03153 0.02545 -0.0194 0.9889 0.0559
-7.250 -0.6474 0.02826 0.02171 -0.0214 0.9778 0.0558
-7.000 -0.6097 0.02605 0.01911 -0.0238 0.9686 0.0571
-6.750 -0.5724 0.02420 0.01691 -0.0259 0.9570 0.0580
-6.500 -0.5340 0.02258 0.01501 -0.0280 0.9451 0.0587
-6.250 -0.4953 0.02079 0.01301 -0.0303 0.9334 0.0597
-6.000 -0.4586 0.01935 0.01157 -0.0323 0.9205 0.0621
-5.750 -0.4265 0.01853 0.01067 -0.0330 0.9059 0.0643
-5.500 -0.3986 0.01779 0.00982 -0.0328 0.8911 0.0661
-5.250 -0.3736 0.01716 0.00909 -0.0320 0.8767 0.0680
-5.000 -0.3501 0.01665 0.00846 -0.0309 0.8627 0.0700
-4.750 -0.3289 0.01592 0.00777 -0.0296 0.8498 0.0737
-4.500 -0.3063 0.01555 0.00736 -0.0284 0.8382 0.0787
-4.250 -0.2848 0.01505 0.00682 -0.0269 0.8279 0.0852
-4.000 -0.2634 0.01460 0.00639 -0.0255 0.8165 0.0970
-3.750 -0.2441 0.01391 0.00590 -0.0238 0.8065 0.1358
-3.500 -0.2244 0.01332 0.00554 -0.0223 0.7974 0.1909
-3.250 -0.2049 0.01281 0.00534 -0.0208 0.7874 0.2622
-3.000 -0.1865 0.01226 0.00509 -0.0190 0.7794 0.3472
-2.750 -0.1737 0.01151 0.00495 -0.0161 0.7698 0.4802
-2.500 -0.1602 0.01088 0.00493 -0.0127 0.7622 0.6336
-2.250 -0.1362 0.01058 0.00507 -0.0111 0.7534 0.7551
-2.000 -0.0998 0.01064 0.00524 -0.0117 0.7461 0.8302
-1.750 -0.0545 0.01092 0.00550 -0.0142 0.7372 0.8722
-1.500 -0.0140 0.01126 0.00572 -0.0158 0.7298 0.8973
-1.250 0.0268 0.01156 0.00591 -0.0178 0.7208 0.9121
-1.000 0.0760 0.01187 0.00607 -0.0215 0.7129 0.9195
-0.750 0.1219 0.01220 0.00630 -0.0245 0.7038 0.9313
-0.500 0.1716 0.01258 0.00655 -0.0283 0.6955 0.9447
-0.250 0.2201 0.01285 0.00672 -0.0320 0.6865 0.9575
0.000 0.2695 0.01292 0.00670 -0.0362 0.6775 0.9655
0.250 0.3125 0.01291 0.00659 -0.0393 0.6689 0.9738
0.500 0.3550 0.01290 0.00653 -0.0424 0.6595 0.9830
0.750 0.4025 0.01270 0.00620 -0.0465 0.6509 0.9900
1.000 0.4458 0.01247 0.00597 -0.0500 0.6405 0.9970
1.250 0.4774 0.01235 0.00578 -0.0511 0.6321 1.0000
1.500 0.4979 0.01232 0.00572 -0.0500 0.6227 1.0000
1.750 0.5186 0.01230 0.00567 -0.0488 0.6138 1.0000
2.000 0.5396 0.01229 0.00560 -0.0477 0.6047 1.0000
2.250 0.5604 0.01228 0.00559 -0.0465 0.5943 1.0000
2.500 0.5819 0.01229 0.00553 -0.0454 0.5857 1.0000
2.750 0.6030 0.01230 0.00556 -0.0443 0.5754 1.0000
3.000 0.6245 0.01233 0.00557 -0.0431 0.5660 1.0000
3.250 0.6461 0.01234 0.00554 -0.0420 0.5560 1.0000
3.500 0.6674 0.01238 0.00560 -0.0408 0.5451 1.0000
3.750 0.6893 0.01244 0.00563 -0.0397 0.5359 1.0000
4.000 0.7111 0.01249 0.00568 -0.0386 0.5255 1.0000
4.250 0.7327 0.01256 0.00578 -0.0374 0.5144 1.0000
4.500 0.7546 0.01265 0.00584 -0.0363 0.5045 1.0000
4.750 0.7764 0.01274 0.00594 -0.0352 0.4939 1.0000
5.000 0.7979 0.01285 0.00609 -0.0340 0.4825 1.0000
5.250 0.8195 0.01298 0.00622 -0.0328 0.4714 1.0000
5.500 0.8412 0.01313 0.00633 -0.0317 0.4608 1.0000
5.750 0.8622 0.01327 0.00654 -0.0304 0.4483 1.0000
6.000 0.8830 0.01343 0.00673 -0.0291 0.4349 1.0000
6.250 0.9032 0.01360 0.00689 -0.0277 0.4200 1.0000
6.500 0.9233 0.01379 0.00709 -0.0262 0.4049 1.0000
6.750 0.9431 0.01400 0.00732 -0.0248 0.3894 1.0000
7.000 0.9624 0.01425 0.00757 -0.0232 0.3727 1.0000
7.250 0.9809 0.01453 0.00783 -0.0216 0.3547 1.0000
7.500 0.9988 0.01485 0.00814 -0.0199 0.3363 1.0000
7.750 1.0164 0.01519 0.00851 -0.0181 0.3148 1.0000
8.000 1.0317 0.01565 0.00890 -0.0161 0.2911 1.0000
8.250 1.0466 0.01614 0.00935 -0.0140 0.2637 1.0000
8.500 1.0587 0.01679 0.00989 -0.0115 0.2327 1.0000
8.750 1.0684 0.01757 0.01053 -0.0088 0.1988 1.0000
9.000 1.0745 0.01856 0.01133 -0.0056 0.1631 1.0000
9.250 1.0756 0.01977 0.01231 -0.0018 0.1330 1.0000
9.500 1.0738 0.02107 0.01347 0.0024 0.1064 1.0000
9.750 1.0718 0.02220 0.01450 0.0067 0.0848 1.0000
10.000 1.0681 0.02327 0.01548 0.0112 0.0736 1.0000
10.250 1.0640 0.02458 0.01672 0.0150 0.0673 1.0000
10.500 1.0634 0.02595 0.01813 0.0179 0.0623 1.0000
10.750 1.0586 0.02781 0.01997 0.0205 0.0589 1.0000
11.000 1.0590 0.02952 0.02176 0.0225 0.0559 1.0000
11.250 1.0606 0.03129 0.02359 0.0241 0.0535 1.0000
11.500 1.0615 0.03320 0.02553 0.0256 0.0514 1.0000
11.750 1.0592 0.03548 0.02776 0.0273 0.0492 1.0000
12.000 1.0652 0.03715 0.02953 0.0284 0.0473 1.0000
12.250 1.0715 0.03884 0.03130 0.0295 0.0456 1.0000
12.500 1.0776 0.04058 0.03308 0.0305 0.0437 1.0000
12.750 1.0856 0.04223 0.03470 0.0317 0.0421 1.0000
13.000 1.1001 0.04371 0.03615 0.0335 0.0403 1.0000
13.250 1.1082 0.04542 0.03801 0.0343 0.0394 1.0000
13.500 1.1150 0.04726 0.03997 0.0350 0.0379 1.0000
13.750 1.1228 0.04909 0.04190 0.0357 0.0367 1.0000
14.000 1.1314 0.05095 0.04384 0.0364 0.0357 1.0000
14.250 1.1447 0.05270 0.04558 0.0374 0.0346 1.0000
14.500 1.1658 0.05509 0.04802 0.0388 0.0336 1.0000
14.750 1.1617 0.05789 0.05106 0.0391 0.0334 1.0000
15.000 1.1562 0.06094 0.05433 0.0391 0.0331 1.0000
15.250 1.1456 0.06445 0.05808 0.0387 0.0326 1.0000
15.500 1.1363 0.06814 0.06199 0.0381 0.0322 1.0000
15.750 1.1258 0.07220 0.06626 0.0372 0.0319 1.0000
16.000 1.1139 0.07655 0.07081 0.0360 0.0315 1.0000
16.250 1.0999 0.08142 0.07589 0.0343 0.0313 1.0000
16.500 1.0831 0.08702 0.08170 0.0320 0.0312 1.0000
16.750 1.0632 0.09336 0.08826 0.0292 0.0313 1.0000
17.000 1.0421 0.10026 0.09536 0.0256 0.0313 1.0000
17.250 1.0182 0.10811 0.10342 0.0214 0.0317 1.0000
17.500 0.9871 0.11785 0.11337 0.0157 0.0317 1.0000
17.750 0.9571 0.12814 0.12383 0.0099 0.0326 1.0000
18.000 0.9251 0.13962 0.13546 0.0030 0.0331 1.0000
18.250 0.8982 0.15060 0.14651 -0.0027 0.0336 1.0000
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