NACA 67 (naca671215-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 67 (naca671215-il) Reynolds number: 200,000 Max Cl/Cd: 42.41 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca671215-il-200000.txt Download as CSV file: xf-naca671215-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3633 0.11614 0.11269 -0.0634 0.9795 0.0715
-12.250 -0.3643 0.11338 0.10993 -0.0634 0.9785 0.0740
-12.000 -0.5183 0.10430 0.10075 -0.0692 0.9853 0.0694
-11.750 -0.5044 0.10268 0.09910 -0.0687 0.9844 0.0709
-11.500 -0.5085 0.09735 0.09378 -0.0720 0.9833 0.0720
-11.250 -0.5313 0.09105 0.08750 -0.0749 0.9809 0.0730
-11.000 -0.5682 0.08412 0.08053 -0.0777 0.9785 0.0730
-10.750 -0.6005 0.07945 0.07579 -0.0774 0.9765 0.0733
-10.500 -0.6301 0.07555 0.07178 -0.0760 0.9744 0.0735
-10.250 -0.6554 0.07237 0.06847 -0.0737 0.9725 0.0742
-10.000 -0.6871 0.07081 0.06683 -0.0676 0.9708 0.0745
-9.750 -0.7244 0.07011 0.06608 -0.0588 0.9691 0.0744
-9.500 -0.7527 0.06862 0.06450 -0.0517 0.9672 0.0748
-9.250 -0.7788 0.06705 0.06280 -0.0447 0.9668 0.0761
-9.000 -0.8983 0.05356 0.04766 -0.0215 0.9684 0.0474
-8.250 -0.9815 0.05155 0.04560 0.0088 1.0000 0.0465
-8.000 -0.9776 0.04760 0.04148 0.0116 1.0000 0.0456
-7.750 -0.9739 0.04456 0.03809 0.0152 1.0000 0.0455
-7.500 -0.9668 0.04161 0.03482 0.0183 1.0000 0.0452
-7.250 -0.9567 0.03888 0.03174 0.0211 1.0000 0.0448
-7.000 -0.9437 0.03647 0.02898 0.0236 1.0000 0.0446
-6.750 -0.9285 0.03454 0.02671 0.0258 1.0000 0.0452
-6.500 -0.9116 0.03299 0.02486 0.0277 1.0000 0.0459
-6.250 -0.8946 0.03205 0.02363 0.0296 1.0000 0.0468
-6.000 -0.8736 0.02987 0.02139 0.0303 1.0000 0.0488
-5.750 -0.8543 0.02899 0.02046 0.0314 1.0000 0.0506
-5.500 -0.8342 0.02812 0.01951 0.0325 1.0000 0.0524
-5.250 -0.8101 0.02739 0.01865 0.0330 0.9993 0.0546
-5.000 -0.7826 0.02667 0.01780 0.0327 0.9975 0.0575
-4.750 -0.7543 0.02615 0.01736 0.0319 0.9953 0.0612
-4.500 -0.7276 0.02593 0.01711 0.0317 0.9935 0.0652
-4.250 -0.7039 0.02529 0.01644 0.0320 0.9902 0.0694
-4.000 -0.6778 0.02504 0.01625 0.0317 0.9869 0.0746
-3.750 -0.6481 0.02524 0.01639 0.0308 0.9843 0.0804
-3.500 -0.6302 0.02458 0.01583 0.0321 0.9804 0.0870
-3.250 -0.6053 0.02435 0.01558 0.0321 0.9758 0.0958
-3.000 -0.5775 0.02438 0.01574 0.0315 0.9728 0.1140
-2.750 -0.5641 0.02344 0.01523 0.0336 0.9681 0.1751
-2.500 -0.5710 0.02074 0.01468 0.0391 0.9627 0.5669
-2.000 -0.5436 0.02277 0.01763 0.0482 0.9512 0.8405
-1.750 -0.5129 0.02449 0.01930 0.0490 0.9468 0.8603
-1.500 -0.4965 0.02533 0.02009 0.0523 0.9403 0.8761
-1.250 -0.4567 0.02697 0.02166 0.0515 0.9338 0.8925
-1.000 -0.0842 0.03377 0.02810 -0.0106 0.9165 0.9241
-0.500 -0.0454 0.03354 0.02781 -0.0088 0.9050 0.9359
-0.250 0.0052 0.03363 0.02785 -0.0139 0.9025 0.9382
0.000 0.0527 0.03384 0.02803 -0.0184 0.9000 0.9406
0.250 0.0365 0.03359 0.02777 -0.0106 0.8901 0.9476
0.500 0.0845 0.03354 0.02770 -0.0153 0.8874 0.9490
0.750 0.1348 0.03361 0.02777 -0.0203 0.8854 0.9504
1.000 0.1415 0.03337 0.02754 -0.0171 0.8758 0.9538
1.250 0.1786 0.03332 0.02749 -0.0194 0.8721 0.9558
1.500 0.2213 0.03333 0.02752 -0.0228 0.8699 0.9572
1.750 0.2164 0.03315 0.02734 -0.0171 0.8586 0.9608
2.000 0.2621 0.03295 0.02718 -0.0210 0.8556 0.9615
2.250 0.3083 0.03283 0.02710 -0.0249 0.8531 0.9622
2.500 0.3211 0.03256 0.02687 -0.0227 0.8424 0.9645
2.750 0.3744 0.03206 0.02644 -0.0276 0.8394 0.9650
3.000 0.3885 0.03170 0.02612 -0.0252 0.8281 0.9665
3.250 0.4499 0.03072 0.02522 -0.0311 0.8246 0.9670
3.500 0.4800 0.02981 0.02439 -0.0310 0.8133 0.9683
3.750 0.6746 0.02395 0.01876 -0.0585 0.8090 0.9663
4.000 0.6805 0.02337 0.01825 -0.0538 0.7966 0.9677
4.250 0.7292 0.02150 0.01651 -0.0565 0.7850 0.9688
4.500 0.7248 0.02104 0.01610 -0.0498 0.7708 0.9696
4.750 0.7021 0.02127 0.01636 -0.0401 0.7546 0.9717
5.000 0.6917 0.02111 0.01624 -0.0326 0.7344 0.9727
5.250 0.7867 0.01855 0.01211 -0.0415 0.4430 0.9723
5.500 0.7625 0.01929 0.01245 -0.0320 0.3697 0.9738
5.750 0.7416 0.02026 0.01297 -0.0235 0.2868 0.9753
6.000 0.7259 0.02133 0.01353 -0.0163 0.2007 0.9765
6.250 0.7198 0.02250 0.01421 -0.0111 0.1299 0.9785
6.500 0.7204 0.02323 0.01476 -0.0068 0.1070 0.9797
6.750 0.7246 0.02379 0.01530 -0.0030 0.0955 0.9809
7.000 0.7284 0.02443 0.01589 0.0008 0.0883 0.9824
7.250 0.7388 0.02493 0.01641 0.0033 0.0816 0.9840
7.500 0.7523 0.02565 0.01709 0.0051 0.0758 0.9849
7.750 0.7692 0.02614 0.01762 0.0064 0.0705 0.9859
8.000 0.7861 0.02710 0.01847 0.0076 0.0654 0.9867
8.250 0.8051 0.02754 0.01903 0.0086 0.0618 0.9878
8.500 0.8243 0.02816 0.01965 0.0094 0.0578 0.9888
8.750 0.8548 0.02934 0.02079 0.0086 0.0538 0.9894
9.000 0.8777 0.03002 0.02159 0.0089 0.0504 0.9908
9.250 0.9003 0.03081 0.02237 0.0091 0.0473 0.9920
9.500 0.9449 0.03270 0.02434 0.0061 0.0444 0.9918
9.750 0.9725 0.03403 0.02590 0.0059 0.0428 0.9926
10.000 0.9974 0.03545 0.02749 0.0059 0.0411 0.9934
10.250 1.0226 0.03694 0.02911 0.0057 0.0398 0.9942
10.500 1.0700 0.04078 0.03300 0.0009 0.0376 0.9937
10.750 1.0713 0.04192 0.03448 0.0046 0.0371 0.9957
11.000 1.0784 0.04400 0.03690 0.0072 0.0368 0.9974
11.250 1.0847 0.04663 0.03985 0.0095 0.0368 0.9991
11.500 1.0773 0.04863 0.04213 0.0142 0.0367 1.0000
11.750 1.0601 0.05026 0.04398 0.0206 0.0367 1.0000
12.000 1.0467 0.05220 0.04609 0.0261 0.0369 1.0000
12.250 1.0231 0.05359 0.04766 0.0330 0.0369 1.0000
12.500 1.0080 0.05574 0.04994 0.0383 0.0372 1.0000
12.750 0.9845 0.05735 0.05169 0.0448 0.0373 1.0000
13.000 0.9749 0.06019 0.05461 0.0489 0.0377 1.0000
13.250 0.9527 0.06107 0.05563 0.0546 0.0378 1.0000
13.500 0.8478 0.06798 0.06344 0.0642 0.0416 1.0000
13.750 0.8174 0.07315 0.06881 0.0654 0.0428 1.0000
14.000 0.7922 0.07843 0.07423 0.0653 0.0436 1.0000
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Polar data table (+)
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