NACA 67 (naca671215-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 67 (naca671215-il) Reynolds number: 100,000 Max Cl/Cd: 25.76 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca671215-il-100000-n5.txt Download as CSV file: xf-naca671215-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 67
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5385 0.09351 0.08814 -0.0794 0.9826 0.0355
-12.500 -0.5749 0.08239 0.07688 -0.0867 0.9794 0.0345
-12.250 -0.6085 0.07448 0.06876 -0.0908 0.9765 0.0342
-12.000 -0.6358 0.06866 0.06271 -0.0923 0.9740 0.0341
-11.750 -0.6623 0.06492 0.05876 -0.0901 0.9698 0.0341
-11.500 -0.6834 0.06142 0.05503 -0.0880 0.9665 0.0341
-11.250 -0.6998 0.05830 0.05163 -0.0856 0.9637 0.0345
-10.750 -0.7371 0.05413 0.04695 -0.0759 0.9553 0.0351
-10.500 -0.7491 0.05196 0.04447 -0.0714 0.9520 0.0355
-10.250 -0.7571 0.04974 0.04190 -0.0672 0.9493 0.0359
-10.000 -0.7734 0.04840 0.04032 -0.0604 0.9452 0.0361
-9.750 -0.7785 0.04639 0.03795 -0.0557 0.9420 0.0365
-9.500 -0.7740 0.04424 0.03538 -0.0527 0.9395 0.0370
-9.250 -0.7618 0.04220 0.03302 -0.0509 0.9379 0.0376
-9.000 -0.7445 0.04064 0.03132 -0.0500 0.9367 0.0384
-8.750 -0.7348 0.03955 0.03010 -0.0474 0.9350 0.0392
-8.500 -0.7312 0.03868 0.02908 -0.0434 0.9325 0.0402
-8.250 -0.7198 0.03767 0.02791 -0.0409 0.9303 0.0415
-8.000 -0.7036 0.03666 0.02665 -0.0392 0.9282 0.0437
-7.750 -0.6823 0.03550 0.02527 -0.0384 0.9269 0.0457
-7.500 -0.6603 0.03451 0.02426 -0.0380 0.9258 0.0475
-7.250 -0.6393 0.03375 0.02343 -0.0372 0.9246 0.0502
-7.000 -0.6159 0.03301 0.02252 -0.0368 0.9236 0.0534
-6.750 -0.5902 0.03210 0.02160 -0.0369 0.9227 0.0563
-6.500 -0.5660 0.03147 0.02096 -0.0369 0.9216 0.0602
-6.250 -0.5592 0.03103 0.02046 -0.0332 0.9188 0.0628
-6.000 -0.5507 0.03061 0.01996 -0.0298 0.9166 0.0654
-5.750 -0.5406 0.03003 0.01944 -0.0270 0.9143 0.0689
-5.500 -0.5257 0.02958 0.01894 -0.0250 0.9119 0.0733
-5.250 -0.5092 0.02912 0.01842 -0.0232 0.9100 0.0777
-5.000 -0.4930 0.02864 0.01797 -0.0215 0.9084 0.0839
-4.750 -0.4730 0.02823 0.01753 -0.0204 0.9070 0.0928
-4.500 -0.4532 0.02782 0.01716 -0.0193 0.9053 0.1055
-4.250 -0.4538 0.02750 0.01690 -0.0142 0.9016 0.1177
-4.000 -0.4434 0.02701 0.01662 -0.0113 0.8987 0.1512
-3.750 -0.4311 0.02621 0.01638 -0.0089 0.8961 0.2429
-3.500 -0.3453 0.02729 0.01998 -0.0160 0.8998 0.7145
-3.250 -0.3624 0.02703 0.01966 -0.0078 0.8950 0.7482
-3.000 -0.3680 0.02682 0.01933 -0.0016 0.8915 0.7801
-2.750 -0.3406 0.02782 0.02020 -0.0005 0.8900 0.8068
-2.500 -0.3395 0.02867 0.02101 0.0058 0.8856 0.8309
-2.250 -0.1885 0.03258 0.02467 -0.0140 0.8919 0.8681
-1.750 -0.1373 0.03289 0.02479 -0.0139 0.8878 0.8818
-1.500 -0.1187 0.03294 0.02477 -0.0126 0.8840 0.8871
-1.250 -0.1139 0.03292 0.02469 -0.0086 0.8800 0.8949
-1.000 -0.0785 0.03293 0.02462 -0.0107 0.8781 0.8970
-0.750 -0.0452 0.03295 0.02457 -0.0124 0.8763 0.8995
-0.500 -0.0140 0.03297 0.02453 -0.0137 0.8747 0.9023
-0.250 -0.0308 0.03290 0.02445 -0.0055 0.8671 0.9102
0.000 -0.0007 0.03290 0.02441 -0.0067 0.8642 0.9120
0.250 0.0313 0.03290 0.02438 -0.0081 0.8617 0.9138
0.500 0.0634 0.03290 0.02436 -0.0096 0.8597 0.9156
0.750 0.0726 0.03291 0.02436 -0.0066 0.8537 0.9195
1.000 0.0802 0.03282 0.02427 -0.0032 0.8482 0.9237
1.250 0.1071 0.03278 0.02422 -0.0035 0.8452 0.9258
1.500 0.1433 0.03276 0.02422 -0.0057 0.8432 0.9268
1.750 0.1510 0.03279 0.02428 -0.0026 0.8348 0.9295
2.000 0.1794 0.03274 0.02426 -0.0032 0.8309 0.9313
2.250 0.2117 0.03266 0.02422 -0.0045 0.8282 0.9327
2.500 0.2088 0.03260 0.02418 0.0009 0.8187 0.9368
2.750 0.2317 0.03241 0.02403 0.0016 0.8141 0.9391
3.000 0.2691 0.03224 0.02393 -0.0004 0.8113 0.9396
3.250 0.2791 0.03223 0.02398 0.0022 0.8009 0.9416
3.500 0.3156 0.03199 0.02383 0.0004 0.7971 0.9425
3.750 0.3294 0.03187 0.02379 0.0026 0.7867 0.9450
4.000 0.3669 0.03134 0.02337 0.0010 0.7816 0.9458
4.250 0.3754 0.03102 0.02312 0.0045 0.7695 0.9484
4.500 0.3842 0.03058 0.02275 0.0082 0.7585 0.9515
4.750 0.4164 0.02983 0.02211 0.0078 0.7473 0.9526
5.750 0.4958 0.02678 0.01948 0.0156 0.6537 0.9598
6.000 0.5544 0.02425 0.01679 0.0133 0.5779 0.9592
6.250 0.6021 0.02337 0.01481 0.0119 0.3969 0.9584
6.500 0.6050 0.02417 0.01507 0.0158 0.3036 0.9615
6.750 0.6118 0.02503 0.01545 0.0187 0.2202 0.9642
7.000 0.6268 0.02596 0.01595 0.0199 0.1520 0.9657
7.250 0.6427 0.02674 0.01651 0.0211 0.1178 0.9673
7.500 0.6578 0.02746 0.01714 0.0225 0.0989 0.9693
7.750 0.6714 0.02817 0.01778 0.0242 0.0874 0.9715
8.000 0.6844 0.02877 0.01845 0.0261 0.0805 0.9741
8.250 0.7020 0.02963 0.01928 0.0269 0.0741 0.9758
8.500 0.7221 0.03038 0.02014 0.0272 0.0683 0.9776
8.750 0.7397 0.03131 0.02106 0.0279 0.0642 0.9796
9.000 0.7589 0.03214 0.02198 0.0286 0.0601 0.9817
9.250 0.7768 0.03296 0.02286 0.0294 0.0563 0.9839
9.500 0.7968 0.03401 0.02386 0.0297 0.0529 0.9855
9.750 0.8199 0.03489 0.02494 0.0296 0.0490 0.9871
10.000 0.8410 0.03589 0.02597 0.0297 0.0460 0.9890
10.250 0.8632 0.03709 0.02722 0.0296 0.0432 0.9908
10.500 0.8878 0.03837 0.02872 0.0295 0.0411 0.9927
10.750 0.9098 0.03971 0.03021 0.0296 0.0390 0.9949
11.000 0.9294 0.04100 0.03153 0.0296 0.0373 0.9976
11.250 0.9511 0.04278 0.03350 0.0294 0.0358 1.0000
11.500 0.9504 0.04395 0.03494 0.0333 0.0345 1.0000
11.750 0.9503 0.04521 0.03641 0.0370 0.0337 1.0000
12.000 0.9472 0.04650 0.03788 0.0410 0.0330 1.0000
12.250 0.9437 0.04787 0.03944 0.0449 0.0326 1.0000
12.500 0.9387 0.04938 0.04113 0.0486 0.0321 1.0000
12.750 0.9353 0.05114 0.04306 0.0517 0.0317 1.0000
13.000 0.9320 0.05318 0.04530 0.0543 0.0313 1.0000
13.250 0.9285 0.05533 0.04761 0.0565 0.0309 1.0000
13.500 0.9232 0.05781 0.05029 0.0585 0.0306 1.0000
13.750 0.9166 0.06050 0.05315 0.0602 0.0303 1.0000
14.000 0.9064 0.06361 0.05647 0.0618 0.0302 1.0000
14.250 0.8932 0.06705 0.06013 0.0630 0.0301 1.0000
14.500 0.8756 0.07111 0.06438 0.0638 0.0299 1.0000
14.750 0.8575 0.07541 0.06890 0.0639 0.0300 1.0000
15.000 0.8331 0.08077 0.07450 0.0630 0.0300 1.0000
15.250 0.7959 0.08851 0.08258 0.0602 0.0303 1.0000
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Polar data table (+)
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