NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 200,000 Max Cl/Cd: 56.69 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653218-il-200000-n5.txt Download as CSV file: xf-naca653218-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7350 0.10047 0.09602 -0.0542 1.0000 0.0240
-16.500 -0.7809 0.08842 0.08364 -0.0613 1.0000 0.0238
-16.250 -0.8051 0.08124 0.07624 -0.0650 1.0000 0.0239
-16.000 -0.8236 0.07544 0.07024 -0.0676 1.0000 0.0239
-15.750 -0.8362 0.07084 0.06547 -0.0693 1.0000 0.0241
-15.500 -0.8490 0.06639 0.06083 -0.0707 1.0000 0.0242
-15.250 -0.8573 0.06277 0.05704 -0.0715 1.0000 0.0244
-15.000 -0.8644 0.05945 0.05356 -0.0721 1.0000 0.0247
-14.750 -0.8701 0.05632 0.05024 -0.0723 1.0000 0.0249
-14.500 -0.8741 0.05352 0.04724 -0.0723 1.0000 0.0253
-14.250 -0.8762 0.05085 0.04439 -0.0720 1.0000 0.0255
-14.000 -0.8757 0.04847 0.04181 -0.0716 1.0000 0.0258
-13.750 -0.8729 0.04627 0.03942 -0.0711 1.0000 0.0261
-13.500 -0.8673 0.04429 0.03725 -0.0705 1.0000 0.0263
-13.250 -0.8603 0.04248 0.03526 -0.0699 1.0000 0.0266
-13.000 -0.8509 0.04086 0.03349 -0.0692 1.0000 0.0269
-12.750 -0.8350 0.03953 0.03213 -0.0688 1.0000 0.0273
-12.500 -0.8206 0.03833 0.03092 -0.0682 1.0000 0.0277
-12.250 -0.8043 0.03710 0.02966 -0.0681 0.9880 0.0281
-12.000 -0.7769 0.03581 0.02829 -0.0703 0.9630 0.0288
-11.750 -0.7489 0.03454 0.02690 -0.0724 0.9482 0.0297
-11.500 -0.7223 0.03340 0.02562 -0.0739 0.9342 0.0305
-11.250 -0.6985 0.03238 0.02448 -0.0745 0.9209 0.0311
-11.000 -0.6776 0.03146 0.02342 -0.0746 0.9082 0.0317
-10.750 -0.6587 0.03052 0.02243 -0.0743 0.8968 0.0323
-10.500 -0.6431 0.02959 0.02148 -0.0735 0.8851 0.0329
-10.250 -0.6282 0.02871 0.02055 -0.0727 0.8748 0.0335
-10.000 -0.6141 0.02786 0.01964 -0.0718 0.8653 0.0343
-9.750 -0.6001 0.02705 0.01876 -0.0708 0.8562 0.0353
-9.500 -0.5865 0.02624 0.01786 -0.0697 0.8481 0.0365
-9.250 -0.5728 0.02546 0.01699 -0.0685 0.8399 0.0375
-9.000 -0.5626 0.02453 0.01602 -0.0670 0.8320 0.0384
-8.750 -0.5516 0.02368 0.01512 -0.0656 0.8246 0.0396
-8.500 -0.5399 0.02290 0.01428 -0.0641 0.8170 0.0409
-8.250 -0.5278 0.02216 0.01345 -0.0626 0.8111 0.0426
-8.000 -0.5146 0.02148 0.01270 -0.0612 0.8041 0.0441
-7.750 -0.5038 0.02071 0.01190 -0.0595 0.7979 0.0463
-7.500 -0.4913 0.02007 0.01119 -0.0578 0.7925 0.0492
-7.250 -0.4791 0.01943 0.01053 -0.0561 0.7859 0.0532
-7.000 -0.4680 0.01880 0.00988 -0.0541 0.7802 0.0588
-6.750 -0.4589 0.01823 0.00930 -0.0516 0.7751 0.0675
-6.500 -0.4508 0.01767 0.00880 -0.0490 0.7692 0.0834
-6.250 -0.4425 0.01693 0.00823 -0.0465 0.7641 0.1163
-6.000 -0.4350 0.01609 0.00762 -0.0439 0.7599 0.1699
-5.750 -0.4286 0.01512 0.00701 -0.0412 0.7549 0.2419
-5.500 -0.4225 0.01407 0.00639 -0.0385 0.7498 0.3325
-5.250 -0.4143 0.01316 0.00604 -0.0357 0.7453 0.4459
-5.000 -0.3929 0.01298 0.00604 -0.0346 0.7418 0.5093
-4.750 -0.3681 0.01297 0.00605 -0.0342 0.7375 0.5400
-4.500 -0.3430 0.01305 0.00615 -0.0337 0.7334 0.5681
-4.250 -0.3178 0.01322 0.00629 -0.0331 0.7297 0.5949
-4.000 -0.2913 0.01348 0.00654 -0.0326 0.7265 0.6137
-3.750 -0.2644 0.01365 0.00662 -0.0323 0.7235 0.6266
-3.500 -0.2367 0.01372 0.00669 -0.0323 0.7194 0.6321
-3.250 -0.2090 0.01373 0.00665 -0.0323 0.7155 0.6368
-3.000 -0.1815 0.01368 0.00650 -0.0325 0.7121 0.6414
-2.750 -0.1539 0.01359 0.00629 -0.0327 0.7092 0.6453
-2.500 -0.1253 0.01357 0.00620 -0.0330 0.7067 0.6476
-2.250 -0.0975 0.01356 0.00620 -0.0331 0.7032 0.6503
-2.000 -0.0697 0.01354 0.00614 -0.0333 0.6996 0.6532
-1.750 -0.0418 0.01350 0.00604 -0.0336 0.6962 0.6564
-1.500 -0.0138 0.01345 0.00591 -0.0339 0.6933 0.6599
-1.250 0.0146 0.01341 0.00580 -0.0342 0.6909 0.6629
-1.000 0.0427 0.01341 0.00580 -0.0344 0.6881 0.6650
-0.750 0.0703 0.01343 0.00584 -0.0346 0.6849 0.6676
-0.500 0.0982 0.01345 0.00585 -0.0348 0.6817 0.6705
-0.250 0.1262 0.01345 0.00583 -0.0351 0.6786 0.6738
0.000 0.1546 0.01343 0.00577 -0.0355 0.6759 0.6770
0.250 0.1833 0.01342 0.00571 -0.0359 0.6737 0.6799
0.500 0.2111 0.01347 0.00579 -0.0361 0.6711 0.6822
0.750 0.2383 0.01353 0.00591 -0.0362 0.6680 0.6850
1.000 0.2659 0.01358 0.00599 -0.0363 0.6648 0.6881
1.250 0.2939 0.01361 0.00603 -0.0366 0.6618 0.6914
1.500 0.3223 0.01364 0.00605 -0.0370 0.6594 0.6947
1.750 0.3510 0.01367 0.00608 -0.0374 0.6572 0.6978
2.000 0.3789 0.01374 0.00620 -0.0375 0.6548 0.7003
2.250 0.4052 0.01384 0.00640 -0.0375 0.6512 0.7034
2.500 0.4322 0.01393 0.00655 -0.0376 0.6481 0.7069
2.750 0.4600 0.01401 0.00666 -0.0378 0.6452 0.7107
3.000 0.4884 0.01406 0.00673 -0.0382 0.6425 0.7144
3.250 0.5169 0.01411 0.00683 -0.0384 0.6401 0.7171
3.500 0.5437 0.01422 0.00705 -0.0385 0.6371 0.7201
3.750 0.5690 0.01435 0.00728 -0.0383 0.6328 0.7239
4.000 0.5960 0.01441 0.00741 -0.0383 0.6284 0.7281
4.500 0.6507 0.01446 0.00759 -0.0384 0.6191 0.7356
4.750 0.6755 0.01449 0.00773 -0.0379 0.6119 0.7391
5.000 0.7023 0.01437 0.00764 -0.0376 0.6027 0.7431
5.250 0.7277 0.01420 0.00747 -0.0371 0.5892 0.7476
5.500 0.7491 0.01410 0.00742 -0.0359 0.5705 0.7519
5.750 0.7684 0.01406 0.00745 -0.0342 0.5466 0.7561
6.000 0.7880 0.01409 0.00748 -0.0328 0.5197 0.7610
6.250 0.8067 0.01423 0.00756 -0.0312 0.4870 0.7664
6.500 0.8171 0.01458 0.00769 -0.0282 0.4322 0.7710
6.750 0.8141 0.01537 0.00816 -0.0232 0.3678 0.7763
7.000 0.8046 0.01630 0.00882 -0.0174 0.3164 0.7830
7.250 0.7967 0.01748 0.00978 -0.0124 0.2678 0.7892
7.500 0.7898 0.01883 0.01091 -0.0080 0.2192 0.7962
7.750 0.7873 0.02020 0.01206 -0.0046 0.1764 0.8040
8.000 0.7861 0.02153 0.01325 -0.0015 0.1392 0.8107
8.250 0.7872 0.02290 0.01444 0.0011 0.1049 0.8186
8.500 0.7899 0.02420 0.01565 0.0034 0.0798 0.8258
8.750 0.7951 0.02543 0.01681 0.0054 0.0633 0.8340
9.000 0.8028 0.02654 0.01792 0.0071 0.0541 0.8421
9.250 0.8112 0.02764 0.01903 0.0088 0.0484 0.8516
9.500 0.8208 0.02867 0.02013 0.0102 0.0447 0.8612
10.000 0.8385 0.03094 0.02252 0.0130 0.0392 0.8842
10.250 0.8484 0.03202 0.02370 0.0142 0.0371 0.8980
10.500 0.8574 0.03323 0.02498 0.0154 0.0356 0.9152
10.750 0.8673 0.03466 0.02649 0.0159 0.0344 0.9382
11.250 0.8935 0.03733 0.02933 0.0156 0.0321 1.0000
11.500 0.9045 0.03877 0.03080 0.0160 0.0311 1.0000
11.750 0.9150 0.04026 0.03232 0.0163 0.0303 1.0000
12.000 0.9241 0.04188 0.03394 0.0167 0.0294 1.0000
12.250 0.9340 0.04347 0.03556 0.0171 0.0287 1.0000
12.500 0.9461 0.04490 0.03706 0.0174 0.0279 1.0000
12.750 0.9574 0.04640 0.03862 0.0177 0.0272 1.0000
13.000 0.9687 0.04792 0.04019 0.0180 0.0265 1.0000
13.250 0.9802 0.04945 0.04177 0.0183 0.0260 1.0000
13.500 0.9915 0.05102 0.04337 0.0185 0.0255 1.0000
13.750 1.0030 0.05259 0.04497 0.0187 0.0251 1.0000
14.000 1.0147 0.05416 0.04655 0.0189 0.0247 1.0000
14.250 1.0275 0.05568 0.04808 0.0192 0.0243 1.0000
14.500 1.0391 0.05735 0.04989 0.0193 0.0239 1.0000
14.750 1.0504 0.05913 0.05179 0.0195 0.0236 1.0000
15.000 1.0603 0.06105 0.05384 0.0195 0.0231 1.0000
15.250 1.0689 0.06311 0.05602 0.0195 0.0228 1.0000
15.500 1.0769 0.06528 0.05832 0.0194 0.0224 1.0000
15.750 1.0827 0.06770 0.06087 0.0192 0.0220 1.0000
16.000 1.0875 0.07024 0.06352 0.0188 0.0216 1.0000
16.250 1.0918 0.07290 0.06630 0.0183 0.0213 1.0000
16.500 1.0956 0.07565 0.06917 0.0178 0.0212 1.0000
16.750 1.0985 0.07855 0.07217 0.0172 0.0209 1.0000
17.000 1.1003 0.08167 0.07541 0.0164 0.0208 1.0000
17.250 1.1009 0.08501 0.07888 0.0155 0.0207 1.0000
17.500 1.1018 0.08835 0.08231 0.0145 0.0204 1.0000
17.750 1.0996 0.09218 0.08628 0.0132 0.0203 1.0000
18.000 1.0899 0.09723 0.09156 0.0112 0.0202 1.0000
18.250 1.0792 0.10263 0.09717 0.0088 0.0202 1.0000
18.500 1.0651 0.10881 0.10359 0.0058 0.0201 1.0000
18.750 1.0491 0.11554 0.11055 0.0023 0.0201 1.0000
19.000 1.0298 0.12321 0.11846 -0.0021 0.0200 1.0000
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