NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 200,000 Max Cl/Cd: 57.35 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653218-il-200000.txt Download as CSV file: xf-naca653218-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(3)-218
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7906 0.06273 0.05789 -0.0744 1.0000 0.0508
-13.000 -0.8053 0.05867 0.05369 -0.0737 1.0000 0.0498
-12.750 -0.8250 0.05469 0.04949 -0.0722 1.0000 0.0485
-12.500 -0.9005 0.05009 0.04417 -0.0648 1.0000 0.0455
-12.250 -0.9361 0.05048 0.04451 -0.0568 0.9983 0.0453
-12.000 -0.9221 0.04792 0.04158 -0.0584 0.9869 0.0449
-11.750 -0.8993 0.04429 0.03762 -0.0606 0.9817 0.0449
-11.500 -0.8704 0.04024 0.03336 -0.0630 0.9776 0.0455
-11.250 -0.8352 0.03744 0.03038 -0.0659 0.9739 0.0461
-11.000 -0.7968 0.03503 0.02780 -0.0689 0.9709 0.0468
-10.750 -0.7588 0.03304 0.02568 -0.0714 0.9658 0.0475
-10.500 -0.7191 0.03131 0.02380 -0.0738 0.9609 0.0484
-10.250 -0.6782 0.02981 0.02216 -0.0765 0.9568 0.0497
-10.000 -0.6459 0.02871 0.02091 -0.0777 0.9482 0.0513
-9.500 -0.5714 0.02655 0.01871 -0.0802 0.9354 0.0544
-9.250 -0.5443 0.02580 0.01797 -0.0804 0.9269 0.0563
-9.000 -0.5253 0.02518 0.01731 -0.0793 0.9158 0.0582
-8.750 -0.5079 0.02460 0.01665 -0.0780 0.9062 0.0603
-8.500 -0.4940 0.02381 0.01586 -0.0763 0.8970 0.0627
-8.250 -0.4832 0.02306 0.01512 -0.0744 0.8878 0.0653
-8.000 -0.4725 0.02235 0.01436 -0.0724 0.8795 0.0684
-7.750 -0.4624 0.02167 0.01362 -0.0704 0.8710 0.0717
-7.500 -0.4590 0.02070 0.01266 -0.0675 0.8628 0.0763
-7.250 -0.4515 0.01999 0.01192 -0.0651 0.8550 0.0835
-7.000 -0.4499 0.01912 0.01109 -0.0617 0.8473 0.0953
-6.750 -0.4580 0.01821 0.01036 -0.0567 0.8404 0.1230
-6.500 -0.4731 0.01680 0.00953 -0.0510 0.8321 0.2161
-6.250 -0.4894 0.01511 0.00862 -0.0448 0.8263 0.3630
-6.000 -0.4868 0.01455 0.00881 -0.0407 0.8193 0.5081
-5.750 -0.4658 0.01474 0.00901 -0.0393 0.8141 0.5555
-5.500 -0.4411 0.01500 0.00920 -0.0383 0.8103 0.5808
-5.250 -0.4155 0.01534 0.00947 -0.0376 0.8066 0.5988
-5.000 -0.3907 0.01569 0.00977 -0.0370 0.8012 0.6131
-4.750 -0.3657 0.01597 0.00994 -0.0363 0.7968 0.6266
-4.500 -0.3375 0.01660 0.01057 -0.0355 0.7934 0.6422
-4.250 -0.3073 0.01765 0.01165 -0.0344 0.7906 0.6591
-4.000 -0.2751 0.01884 0.01295 -0.0336 0.7858 0.6686
-3.750 -0.2513 0.01908 0.01311 -0.0329 0.7814 0.6789
-3.500 -0.2206 0.01946 0.01347 -0.0327 0.7781 0.6826
-3.250 -0.1918 0.01961 0.01355 -0.0326 0.7753 0.6867
-3.000 -0.1712 0.01920 0.01298 -0.0324 0.7721 0.6950
-2.750 -0.1450 0.01939 0.01320 -0.0321 0.7672 0.6974
-2.500 -0.1177 0.01949 0.01327 -0.0319 0.7633 0.7002
-2.250 -0.0904 0.01948 0.01321 -0.0319 0.7602 0.7036
-2.000 -0.0646 0.01927 0.01291 -0.0321 0.7576 0.7083
-1.750 -0.0403 0.01899 0.01252 -0.0323 0.7550 0.7133
-1.500 -0.0164 0.01913 0.01270 -0.0319 0.7502 0.7155
-1.250 0.0095 0.01917 0.01274 -0.0318 0.7463 0.7182
-1.000 0.0364 0.01914 0.01268 -0.0319 0.7433 0.7214
-0.750 0.0636 0.01899 0.01247 -0.0322 0.7409 0.7252
-0.500 0.0906 0.01875 0.01212 -0.0329 0.7389 0.7301
-0.250 0.1128 0.01898 0.01243 -0.0323 0.7344 0.7324
0.000 0.1372 0.01911 0.01259 -0.0320 0.7303 0.7350
0.250 0.1636 0.01913 0.01261 -0.0321 0.7272 0.7378
0.500 0.1911 0.01910 0.01256 -0.0324 0.7248 0.7413
0.750 0.2197 0.01899 0.01240 -0.0330 0.7227 0.7459
1.000 0.2443 0.01910 0.01252 -0.0330 0.7195 0.7491
1.250 0.2642 0.01945 0.01296 -0.0322 0.7145 0.7517
1.500 0.2894 0.01959 0.01314 -0.0321 0.7113 0.7546
1.750 0.3170 0.01960 0.01316 -0.0323 0.7086 0.7582
2.000 0.3465 0.01953 0.01307 -0.0330 0.7064 0.7626
2.250 0.3765 0.01949 0.01302 -0.0337 0.7046 0.7663
2.500 0.3884 0.02018 0.01386 -0.0318 0.6980 0.7693
2.750 0.4127 0.02036 0.01410 -0.0315 0.6942 0.7725
3.000 0.4416 0.02034 0.01410 -0.0319 0.6916 0.7763
3.250 0.4733 0.02020 0.01397 -0.0328 0.6893 0.7810
3.500 0.5056 0.02007 0.01385 -0.0335 0.6873 0.7846
3.750 0.5118 0.02089 0.01485 -0.0308 0.6787 0.7884
4.000 0.5420 0.02074 0.01475 -0.0311 0.6753 0.7921
4.250 0.5759 0.02045 0.01449 -0.0320 0.6727 0.7965
4.500 0.6055 0.02037 0.01444 -0.0325 0.6689 0.8011
4.750 0.6201 0.02069 0.01492 -0.0306 0.6610 0.8049
5.000 0.6577 0.01997 0.01423 -0.0314 0.6566 0.8089
5.250 0.6872 0.01953 0.01383 -0.0314 0.6490 0.8141
5.500 0.7292 0.01816 0.01239 -0.0325 0.6384 0.8185
5.750 0.7559 0.01724 0.01149 -0.0313 0.6232 0.8222
6.000 0.7801 0.01669 0.01100 -0.0300 0.6091 0.8271
6.250 0.8055 0.01634 0.01070 -0.0295 0.5970 0.8332
6.500 0.8292 0.01599 0.01041 -0.0283 0.5843 0.8381
6.750 0.8488 0.01574 0.01025 -0.0265 0.5687 0.8437
7.000 0.8662 0.01559 0.01018 -0.0247 0.5479 0.8511
7.250 0.8793 0.01543 0.01005 -0.0217 0.5214 0.8567
7.500 0.8866 0.01546 0.01002 -0.0180 0.4770 0.8644
7.750 0.8770 0.01585 0.01008 -0.0114 0.4087 0.8733
8.000 0.8563 0.01693 0.01078 -0.0039 0.3446 0.8855
8.250 0.8351 0.01835 0.01190 0.0029 0.2864 0.8985
8.500 0.8138 0.02005 0.01329 0.0090 0.2263 0.9135
8.750 0.7930 0.02206 0.01494 0.0143 0.1621 0.9316
9.000 0.7807 0.02430 0.01681 0.0175 0.1050 0.9527
9.250 0.7898 0.02658 0.01891 0.0166 0.0786 0.9759
9.500 0.8010 0.02822 0.02051 0.0161 0.0690 1.0000
9.750 0.8091 0.02994 0.02217 0.0162 0.0641 1.0000
10.000 0.8227 0.03126 0.02352 0.0162 0.0599 1.0000
10.250 0.8323 0.03284 0.02503 0.0166 0.0568 1.0000
10.500 0.8448 0.03422 0.02641 0.0171 0.0545 1.0000
10.750 0.8600 0.03539 0.02760 0.0175 0.0523 1.0000
11.000 0.8753 0.03655 0.02873 0.0178 0.0501 1.0000
11.250 0.8933 0.03763 0.02971 0.0183 0.0483 1.0000
11.500 0.9139 0.03860 0.03072 0.0187 0.0465 1.0000
11.750 0.9363 0.03950 0.03166 0.0190 0.0453 1.0000
12.000 0.9592 0.04046 0.03266 0.0192 0.0439 1.0000
12.250 0.9845 0.04141 0.03363 0.0193 0.0429 1.0000
12.500 1.0129 0.04242 0.03461 0.0192 0.0418 1.0000
12.750 1.0579 0.04380 0.03598 0.0182 0.0405 1.0000
13.000 1.0692 0.04542 0.03781 0.0189 0.0399 1.0000
13.250 1.0842 0.04721 0.03980 0.0194 0.0394 1.0000
13.500 1.0978 0.04924 0.04205 0.0199 0.0389 1.0000
13.750 1.1102 0.05158 0.04460 0.0204 0.0387 1.0000
14.000 1.1172 0.05418 0.04744 0.0211 0.0385 1.0000
14.250 1.1211 0.05707 0.05058 0.0218 0.0385 1.0000
14.500 1.1197 0.06030 0.05406 0.0226 0.0385 1.0000
14.750 1.1134 0.06386 0.05788 0.0233 0.0386 1.0000
15.000 1.1040 0.06773 0.06200 0.0238 0.0388 1.0000
15.250 1.0916 0.07196 0.06647 0.0241 0.0391 1.0000
15.500 1.0754 0.07655 0.07129 0.0239 0.0393 1.0000
15.750 1.0594 0.08137 0.07631 0.0234 0.0396 1.0000
16.000 1.0402 0.08670 0.08185 0.0223 0.0398 1.0000
16.250 1.0253 0.09216 0.08747 0.0209 0.0401 1.0000
16.500 1.0078 0.09803 0.09349 0.0190 0.0404 1.0000
16.750 1.0051 0.10318 0.09874 0.0177 0.0408 1.0000
17.000 0.5545 0.16252 0.15955 -0.0182 0.0765 1.0000
17.250 0.5722 0.16593 0.16298 -0.0179 0.0755 1.0000
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