NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 500,000 Max Cl/Cd: 76.26 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212-il-500000.txt Download as CSV file: xf-naca651212-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5502 0.08809 0.08579 -0.0391 1.0000 0.0238
-10.750 -0.5912 0.07182 0.06946 -0.0523 1.0000 0.0233
-10.500 -0.6219 0.06465 0.06217 -0.0565 1.0000 0.0232
-10.250 -0.6432 0.06031 0.05772 -0.0576 1.0000 0.0233
-10.000 -0.6501 0.05823 0.05562 -0.0570 1.0000 0.0236
-9.750 -0.6664 0.05571 0.05303 -0.0550 1.0000 0.0237
-9.500 -0.6796 0.05285 0.05005 -0.0526 1.0000 0.0238
-9.250 -0.6808 0.05116 0.04832 -0.0507 1.0000 0.0244
-9.000 -0.6903 0.04927 0.04636 -0.0471 1.0000 0.0248
-8.750 -0.6779 0.04582 0.04268 -0.0484 0.9930 0.0261
-8.250 -0.6555 0.03084 0.02605 -0.0501 0.9751 0.0225
-8.000 -0.6230 0.02969 0.02471 -0.0517 0.9706 0.0222
-7.750 -0.6021 0.02602 0.02066 -0.0518 0.9612 0.0223
-7.500 -0.5789 0.02281 0.01712 -0.0518 0.9530 0.0224
-7.250 -0.5559 0.02015 0.01421 -0.0514 0.9442 0.0228
-7.000 -0.5328 0.01855 0.01249 -0.0508 0.9350 0.0232
-6.750 -0.5094 0.01748 0.01133 -0.0501 0.9270 0.0239
-6.500 -0.4865 0.01667 0.01046 -0.0494 0.9176 0.0247
-6.250 -0.4630 0.01606 0.00978 -0.0487 0.9095 0.0258
-6.000 -0.4395 0.01539 0.00902 -0.0479 0.9011 0.0268
-5.750 -0.4160 0.01467 0.00822 -0.0472 0.8934 0.0276
-5.500 -0.3923 0.01409 0.00756 -0.0465 0.8857 0.0284
-5.250 -0.3679 0.01366 0.00707 -0.0459 0.8783 0.0290
-5.000 -0.3486 0.01248 0.00580 -0.0446 0.8705 0.0307
-4.750 -0.3250 0.01199 0.00528 -0.0441 0.8632 0.0328
-4.500 -0.3004 0.01160 0.00485 -0.0436 0.8562 0.0351
-4.250 -0.2752 0.01126 0.00443 -0.0432 0.8498 0.0370
-4.000 -0.2507 0.01076 0.00386 -0.0428 0.8428 0.0407
-3.750 -0.2250 0.01044 0.00350 -0.0425 0.8369 0.0463
-3.500 -0.1993 0.01007 0.00316 -0.0422 0.8299 0.0596
-3.250 -0.1809 0.00853 0.00255 -0.0416 0.8238 0.2921
-3.000 -0.1618 0.00723 0.00225 -0.0409 0.8171 0.5562
-2.750 -0.1353 0.00709 0.00224 -0.0406 0.8114 0.6108
-2.500 -0.1078 0.00707 0.00221 -0.0405 0.8060 0.6371
-2.250 -0.0802 0.00707 0.00221 -0.0405 0.7998 0.6605
-2.000 -0.0530 0.00710 0.00227 -0.0402 0.7946 0.6853
-1.750 -0.0258 0.00720 0.00236 -0.0399 0.7892 0.7080
-1.500 0.0018 0.00725 0.00241 -0.0398 0.7836 0.7216
-1.250 0.0296 0.00727 0.00242 -0.0397 0.7787 0.7301
-1.000 0.0581 0.00727 0.00239 -0.0399 0.7733 0.7358
-0.750 0.0865 0.00725 0.00236 -0.0401 0.7680 0.7404
-0.500 0.1148 0.00727 0.00234 -0.0402 0.7635 0.7452
-0.250 0.1434 0.00727 0.00233 -0.0405 0.7581 0.7508
0.000 0.1717 0.00726 0.00233 -0.0406 0.7530 0.7554
0.250 0.2001 0.00730 0.00234 -0.0407 0.7487 0.7605
0.500 0.2286 0.00731 0.00237 -0.0410 0.7436 0.7661
0.750 0.2568 0.00731 0.00239 -0.0411 0.7386 0.7710
1.000 0.2852 0.00735 0.00243 -0.0413 0.7343 0.7763
1.250 0.3137 0.00739 0.00248 -0.0415 0.7295 0.7823
1.500 0.3417 0.00739 0.00254 -0.0416 0.7245 0.7872
1.750 0.3700 0.00744 0.00260 -0.0417 0.7199 0.7931
2.000 0.3979 0.00745 0.00265 -0.0418 0.7126 0.7990
2.250 0.4251 0.00745 0.00265 -0.0415 0.7026 0.8043
2.500 0.4521 0.00743 0.00262 -0.0413 0.6888 0.8109
2.750 0.4782 0.00737 0.00260 -0.0408 0.6690 0.8167
3.000 0.5044 0.00737 0.00260 -0.0404 0.6485 0.8231
3.250 0.5308 0.00742 0.00262 -0.0401 0.6286 0.8295
3.500 0.5568 0.00747 0.00271 -0.0397 0.6056 0.8357
3.750 0.5819 0.00763 0.00278 -0.0391 0.5686 0.8431
4.000 0.6020 0.00807 0.00293 -0.0377 0.4797 0.8499
4.250 0.6099 0.00977 0.00362 -0.0349 0.2608 0.8588
4.500 0.6183 0.01146 0.00442 -0.0322 0.0731 0.8673
4.750 0.6384 0.01209 0.00492 -0.0309 0.0445 0.8755
5.000 0.6605 0.01249 0.00538 -0.0299 0.0385 0.8844
5.250 0.6804 0.01299 0.00592 -0.0285 0.0342 0.8932
5.500 0.6997 0.01355 0.00657 -0.0270 0.0319 0.9034
5.750 0.7196 0.01393 0.00703 -0.0256 0.0300 0.9138
6.000 0.7378 0.01434 0.00749 -0.0238 0.0282 0.9252
6.250 0.7533 0.01485 0.00805 -0.0216 0.0266 0.9396
6.500 0.7646 0.01584 0.00913 -0.0188 0.0253 0.9595
6.750 0.7919 0.01676 0.01014 -0.0193 0.0246 0.9794
7.000 0.8199 0.01750 0.01094 -0.0200 0.0239 1.0000
7.250 0.8436 0.01834 0.01183 -0.0197 0.0231 1.0000
7.500 0.8673 0.01922 0.01275 -0.0195 0.0223 1.0000
7.750 0.8910 0.02002 0.01359 -0.0192 0.0214 1.0000
8.000 0.9145 0.02093 0.01454 -0.0189 0.0207 1.0000
8.250 0.9383 0.02206 0.01570 -0.0187 0.0202 1.0000
8.500 0.9630 0.02361 0.01730 -0.0187 0.0197 1.0000
8.750 0.9892 0.02610 0.01992 -0.0190 0.0193 1.0000
9.000 1.0124 0.02906 0.02311 -0.0188 0.0191 1.0000
9.250 1.0303 0.03259 0.02695 -0.0179 0.0190 1.0000
9.500 1.0437 0.03345 0.02807 -0.0161 0.0186 1.0000
9.750 1.0572 0.03500 0.02988 -0.0144 0.0182 1.0000
10.000 1.0646 0.03812 0.03332 -0.0123 0.0182 1.0000
10.250 1.0657 0.04200 0.03750 -0.0098 0.0184 1.0000
12.000 0.8393 0.07510 0.07253 0.0076 0.0250 1.0000
12.250 0.8293 0.07807 0.07560 0.0067 0.0252 1.0000
12.500 0.8123 0.08235 0.08000 0.0048 0.0254 1.0000
12.750 0.6791 0.11396 0.11206 -0.0173 0.0272 1.0000
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Polar data table (+)
Polar graphs
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