NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 200,000 Max Cl/Cd: 47.11 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66209-il-200000-n5.txt Download as CSV file: xf-naca66209-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5149 0.08660 0.08302 -0.0368 1.0000 0.0160
-9.250 -0.5197 0.08142 0.07789 -0.0402 1.0000 0.0160
-9.000 -0.5271 0.07621 0.07275 -0.0443 1.0000 0.0157
-8.750 -0.5391 0.07184 0.06839 -0.0465 1.0000 0.0153
-8.500 -0.5553 0.06839 0.06494 -0.0461 1.0000 0.0153
-8.250 -0.5696 0.06492 0.06144 -0.0446 1.0000 0.0151
-8.000 -0.5836 0.06224 0.05873 -0.0418 1.0000 0.0148
-7.750 -0.5813 0.05713 0.05343 -0.0434 0.9939 0.0145
-7.500 -0.5686 0.05116 0.04716 -0.0462 0.9868 0.0141
-7.250 -0.5540 0.04563 0.04124 -0.0479 0.9800 0.0139
-7.000 -0.5352 0.04025 0.03542 -0.0493 0.9754 0.0140
-6.750 -0.5166 0.03593 0.03068 -0.0495 0.9692 0.0141
-6.500 -0.4929 0.03180 0.02603 -0.0500 0.9653 0.0149
-6.250 -0.4699 0.02898 0.02273 -0.0495 0.9596 0.0165
-6.000 -0.4429 0.02686 0.02012 -0.0496 0.9554 0.0174
-5.750 -0.4167 0.02351 0.01628 -0.0500 0.9524 0.0181
-5.500 -0.3930 0.02151 0.01404 -0.0497 0.9474 0.0190
-5.000 -0.3368 0.01952 0.01171 -0.0505 0.9403 0.0228
-4.750 -0.3078 0.01820 0.01020 -0.0508 0.9373 0.0238
-4.500 -0.2829 0.01717 0.00905 -0.0502 0.9322 0.0250
-4.250 -0.2559 0.01630 0.00807 -0.0501 0.9285 0.0262
-4.000 -0.2277 0.01574 0.00744 -0.0503 0.9255 0.0276
-3.750 -0.2060 0.01466 0.00632 -0.0495 0.9209 0.0311
-3.500 -0.1818 0.01408 0.00570 -0.0491 0.9164 0.0335
-3.250 -0.1556 0.01359 0.00513 -0.0489 0.9128 0.0366
-3.000 -0.1294 0.01323 0.00466 -0.0488 0.9093 0.0401
-2.750 -0.1056 0.01284 0.00426 -0.0482 0.9046 0.0497
-2.500 -0.0800 0.01246 0.00392 -0.0480 0.9010 0.0703
-2.250 -0.0654 0.01051 0.00348 -0.0469 0.8973 0.4424
-2.000 -0.0552 0.00978 0.00395 -0.0426 0.8921 0.7480
-1.750 -0.0342 0.00997 0.00422 -0.0404 0.8882 0.8035
-1.500 -0.0099 0.01010 0.00430 -0.0391 0.8852 0.8279
-1.250 0.0150 0.01022 0.00440 -0.0380 0.8829 0.8445
-1.000 0.0353 0.01042 0.00460 -0.0360 0.8784 0.8618
-0.750 0.0591 0.01051 0.00465 -0.0349 0.8747 0.8727
-0.500 0.0866 0.01050 0.00459 -0.0349 0.8718 0.8766
-0.250 0.1149 0.01048 0.00452 -0.0351 0.8696 0.8807
0.000 0.1407 0.01051 0.00454 -0.0350 0.8659 0.8843
0.250 0.1668 0.01053 0.00457 -0.0347 0.8621 0.8877
0.500 0.1940 0.01054 0.00458 -0.0347 0.8590 0.8916
0.750 0.2221 0.01053 0.00457 -0.0349 0.8563 0.8956
1.000 0.2480 0.01054 0.00462 -0.0346 0.8514 0.8990
1.250 0.2742 0.01054 0.00466 -0.0343 0.8463 0.9027
1.500 0.3022 0.01051 0.00467 -0.0343 0.8424 0.9069
1.750 0.3277 0.01052 0.00475 -0.0340 0.8367 0.9116
2.000 0.3553 0.01040 0.00467 -0.0336 0.8286 0.9147
2.250 0.3799 0.01010 0.00441 -0.0323 0.8079 0.9189
2.500 0.4046 0.00983 0.00413 -0.0310 0.7824 0.9238
2.750 0.4290 0.00965 0.00394 -0.0297 0.7477 0.9282
3.000 0.4508 0.00957 0.00360 -0.0277 0.6503 0.9332
3.250 0.4539 0.01092 0.00364 -0.0227 0.3847 0.9415
3.500 0.4605 0.01274 0.00427 -0.0198 0.1209 0.9506
3.750 0.4827 0.01361 0.00478 -0.0194 0.0512 0.9570
4.000 0.5092 0.01407 0.00526 -0.0195 0.0399 0.9637
4.250 0.5374 0.01470 0.00594 -0.0200 0.0340 0.9695
4.750 0.5949 0.01601 0.00749 -0.0213 0.0286 0.9827
5.000 0.6234 0.01686 0.00840 -0.0219 0.0267 0.9914
5.250 0.6469 0.01781 0.00937 -0.0217 0.0245 1.0000
5.500 0.6652 0.01915 0.01073 -0.0203 0.0227 1.0000
5.750 0.6881 0.02007 0.01175 -0.0197 0.0219 1.0000
6.000 0.7126 0.02125 0.01309 -0.0192 0.0211 1.0000
6.250 0.7378 0.02268 0.01468 -0.0188 0.0204 1.0000
6.500 0.7631 0.02439 0.01662 -0.0184 0.0197 1.0000
6.750 0.7869 0.02591 0.01837 -0.0178 0.0184 1.0000
7.000 0.8091 0.02702 0.01964 -0.0173 0.0169 1.0000
7.250 0.8303 0.02876 0.02163 -0.0165 0.0161 1.0000
7.500 0.8495 0.03077 0.02388 -0.0156 0.0155 1.0000
7.750 0.8657 0.03349 0.02694 -0.0143 0.0150 1.0000
8.000 0.8743 0.03786 0.03176 -0.0122 0.0145 1.0000
8.250 0.8845 0.04066 0.03502 -0.0099 0.0139 1.0000
8.500 0.8931 0.04411 0.03897 -0.0074 0.0126 1.0000
8.750 0.8943 0.04839 0.04363 -0.0047 0.0124 1.0000
9.000 0.8912 0.05276 0.04834 -0.0020 0.0122 1.0000
9.250 0.8840 0.05709 0.05295 0.0006 0.0121 1.0000
9.500 0.8720 0.06108 0.05717 0.0033 0.0120 1.0000
9.750 0.8552 0.06493 0.06118 0.0059 0.0120 1.0000
10.000 0.8369 0.06909 0.06549 0.0071 0.0121 1.0000
10.250 0.8177 0.07390 0.07042 0.0067 0.0121 1.0000
10.500 0.7990 0.07944 0.07606 0.0046 0.0123 1.0000
10.750 0.7805 0.08664 0.08334 0.0001 0.0125 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66-209 (naca66209-il)