NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 100,000 Max Cl/Cd: 31.86 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653218-il-100000-n5.txt Download as CSV file: xf-naca653218-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6035 0.11549 0.10983 -0.0495 1.0000 0.0374
-15.500 -0.6400 0.10330 0.09751 -0.0569 1.0000 0.0370
-15.250 -0.6761 0.09319 0.08722 -0.0629 1.0000 0.0367
-15.000 -0.7075 0.08522 0.07906 -0.0672 1.0000 0.0366
-14.750 -0.7317 0.07907 0.07272 -0.0700 1.0000 0.0364
-14.500 -0.7552 0.07360 0.06703 -0.0719 1.0000 0.0364
-14.250 -0.7751 0.06889 0.06209 -0.0730 1.0000 0.0365
-14.000 -0.7922 0.06478 0.05774 -0.0735 1.0000 0.0366
-13.750 -0.8070 0.06110 0.05381 -0.0735 1.0000 0.0368
-13.500 -0.8179 0.05787 0.05034 -0.0730 1.0000 0.0369
-13.250 -0.8290 0.05489 0.04708 -0.0721 1.0000 0.0373
-13.000 -0.8354 0.05231 0.04425 -0.0711 1.0000 0.0377
-12.750 -0.8272 0.05031 0.04221 -0.0705 1.0000 0.0383
-12.500 -0.8204 0.04852 0.04034 -0.0697 1.0000 0.0389
-12.250 -0.8137 0.04675 0.03846 -0.0687 1.0000 0.0394
-12.000 -0.8061 0.04508 0.03667 -0.0675 1.0000 0.0399
-11.750 -0.7987 0.04362 0.03511 -0.0660 1.0000 0.0404
-11.500 -0.7925 0.04239 0.03377 -0.0640 0.9986 0.0409
-11.250 -0.7620 0.04052 0.03171 -0.0659 0.9857 0.0418
-11.000 -0.7313 0.03890 0.02986 -0.0677 0.9760 0.0432
-10.750 -0.6984 0.03746 0.02827 -0.0696 0.9679 0.0447
-10.500 -0.6647 0.03621 0.02705 -0.0715 0.9605 0.0462
-10.250 -0.6332 0.03509 0.02588 -0.0731 0.9519 0.0478
-10.000 -0.6014 0.03404 0.02474 -0.0745 0.9443 0.0495
-9.750 -0.5737 0.03310 0.02370 -0.0753 0.9349 0.0510
-9.500 -0.5510 0.03209 0.02268 -0.0757 0.9253 0.0532
-9.250 -0.5309 0.03114 0.02171 -0.0758 0.9157 0.0557
-9.000 -0.5144 0.03032 0.02080 -0.0752 0.9048 0.0584
-8.750 -0.4994 0.02942 0.01984 -0.0743 0.8955 0.0614
-8.500 -0.4874 0.02854 0.01893 -0.0730 0.8856 0.0645
-8.250 -0.4745 0.02774 0.01805 -0.0717 0.8772 0.0691
-8.000 -0.4644 0.02686 0.01717 -0.0701 0.8683 0.0747
-7.750 -0.4539 0.02603 0.01633 -0.0684 0.8603 0.0831
-7.500 -0.4461 0.02512 0.01549 -0.0664 0.8518 0.0962
-7.250 -0.4410 0.02409 0.01461 -0.0640 0.8447 0.1227
-7.000 -0.4420 0.02297 0.01376 -0.0609 0.8361 0.1677
-6.750 -0.4495 0.02185 0.01293 -0.0564 0.8295 0.2244
-6.500 -0.4587 0.02080 0.01228 -0.0517 0.8208 0.2961
-6.250 -0.4627 0.01985 0.01192 -0.0471 0.8144 0.3928
-6.000 -0.4463 0.02001 0.01254 -0.0444 0.8095 0.4901
-5.750 -0.4309 0.02012 0.01263 -0.0423 0.8030 0.5295
-5.250 -0.3943 0.02082 0.01315 -0.0383 0.7945 0.5941
-5.000 -0.3626 0.02233 0.01472 -0.0369 0.7898 0.6183
-4.750 -0.3376 0.02295 0.01525 -0.0357 0.7848 0.6321
-4.500 -0.3148 0.02313 0.01529 -0.0346 0.7805 0.6429
-4.250 -0.2853 0.02337 0.01541 -0.0343 0.7774 0.6487
-4.000 -0.2595 0.02354 0.01550 -0.0339 0.7730 0.6536
-3.750 -0.2460 0.02315 0.01497 -0.0325 0.7677 0.6626
-3.500 -0.2170 0.02330 0.01505 -0.0324 0.7642 0.6655
-3.250 -0.1893 0.02330 0.01494 -0.0322 0.7611 0.6692
-3.000 -0.1661 0.02311 0.01464 -0.0318 0.7578 0.6742
-2.750 -0.1505 0.02284 0.01430 -0.0307 0.7521 0.6805
-2.500 -0.1242 0.02288 0.01428 -0.0305 0.7483 0.6830
-2.250 -0.0979 0.02284 0.01417 -0.0304 0.7453 0.6860
-2.000 -0.0721 0.02269 0.01394 -0.0303 0.7427 0.6899
-1.750 -0.0532 0.02248 0.01364 -0.0297 0.7385 0.6955
-1.500 -0.0318 0.02248 0.01362 -0.0291 0.7337 0.6988
-1.250 -0.0061 0.02252 0.01363 -0.0289 0.7302 0.7014
-1.000 0.0203 0.02248 0.01354 -0.0288 0.7274 0.7045
-0.750 0.0468 0.02235 0.01335 -0.0289 0.7252 0.7081
-0.500 0.0662 0.02232 0.01329 -0.0284 0.7210 0.7134
-0.250 0.0869 0.02246 0.01344 -0.0276 0.7162 0.7166
0.000 0.1119 0.02252 0.01350 -0.0274 0.7128 0.7192
0.250 0.1385 0.02251 0.01348 -0.0274 0.7102 0.7221
0.500 0.1659 0.02246 0.01340 -0.0276 0.7082 0.7258
0.750 0.1860 0.02257 0.01351 -0.0271 0.7041 0.7308
1.000 0.2042 0.02284 0.01383 -0.0260 0.6990 0.7343
1.250 0.2283 0.02297 0.01399 -0.0257 0.6957 0.7371
1.500 0.2547 0.02302 0.01406 -0.0257 0.6932 0.7402
1.750 0.2832 0.02299 0.01404 -0.0260 0.6911 0.7441
2.000 0.3009 0.02328 0.01437 -0.0252 0.6864 0.7494
2.250 0.3168 0.02371 0.01488 -0.0238 0.6812 0.7528
2.500 0.3410 0.02387 0.01510 -0.0234 0.6779 0.7561
2.750 0.3690 0.02388 0.01515 -0.0236 0.6755 0.7597
3.000 0.3991 0.02383 0.01513 -0.0242 0.6735 0.7639
3.250 0.4041 0.02465 0.01605 -0.0217 0.6659 0.7692
3.500 0.4252 0.02490 0.01639 -0.0208 0.6617 0.7728
3.750 0.4531 0.02492 0.01649 -0.0208 0.6590 0.7769
4.000 0.4850 0.02480 0.01643 -0.0215 0.6569 0.7814
4.250 0.4863 0.02573 0.01747 -0.0185 0.6479 0.7871
4.500 0.5109 0.02579 0.01763 -0.0180 0.6438 0.7908
4.750 0.5433 0.02558 0.01751 -0.0185 0.6412 0.7952
5.000 0.5786 0.02528 0.01731 -0.0195 0.6388 0.8003
5.250 0.5724 0.02636 0.01852 -0.0152 0.6276 0.8066
5.500 0.6074 0.02594 0.01821 -0.0158 0.6245 0.8109
6.000 0.6453 0.02605 0.01856 -0.0132 0.6094 0.8227
6.250 0.6765 0.02546 0.01809 -0.0130 0.6027 0.8275
6.500 0.6931 0.02536 0.01813 -0.0111 0.5927 0.8346
6.750 0.7056 0.02511 0.01799 -0.0082 0.5802 0.8416
7.000 0.7244 0.02421 0.01716 -0.0057 0.5623 0.8488
7.250 0.7378 0.02357 0.01655 -0.0027 0.5376 0.8570
7.500 0.7336 0.02422 0.01729 0.0016 0.5124 0.8669
7.750 0.7380 0.02467 0.01779 0.0046 0.4832 0.8769
8.000 0.7563 0.02441 0.01745 0.0065 0.4400 0.8871
8.250 0.7717 0.02422 0.01679 0.0092 0.3660 0.8971
8.500 0.7673 0.02551 0.01773 0.0127 0.3057 0.9115
8.750 0.7614 0.02727 0.01919 0.0155 0.2506 0.9288
9.000 0.7604 0.02932 0.02093 0.0167 0.1931 0.9495
9.250 0.7661 0.03140 0.02267 0.0164 0.1374 0.9823
9.500 0.7703 0.03312 0.02412 0.0172 0.1035 1.0000
9.750 0.7773 0.03479 0.02559 0.0179 0.0832 1.0000
10.000 0.7861 0.03636 0.02707 0.0184 0.0720 1.0000
10.250 0.7956 0.03790 0.02857 0.0189 0.0653 1.0000
10.500 0.8061 0.03936 0.03005 0.0194 0.0600 1.0000
10.750 0.8156 0.04092 0.03159 0.0198 0.0563 1.0000
11.000 0.8260 0.04244 0.03313 0.0203 0.0533 1.0000
11.250 0.8368 0.04393 0.03468 0.0207 0.0507 1.0000
11.500 0.8475 0.04546 0.03621 0.0211 0.0488 1.0000
11.750 0.8584 0.04700 0.03773 0.0216 0.0471 1.0000
12.000 0.8721 0.04834 0.03917 0.0219 0.0451 1.0000
12.250 0.8855 0.04974 0.04061 0.0223 0.0432 1.0000
12.500 0.8992 0.05115 0.04203 0.0226 0.0418 1.0000
12.750 0.9146 0.05249 0.04331 0.0229 0.0407 1.0000
13.000 0.9329 0.05372 0.04463 0.0233 0.0397 1.0000
13.250 0.9511 0.05506 0.04609 0.0236 0.0387 1.0000
13.500 0.9674 0.05658 0.04774 0.0238 0.0377 1.0000
13.750 0.9821 0.05823 0.04950 0.0240 0.0367 1.0000
14.000 0.9952 0.06000 0.05134 0.0241 0.0357 1.0000
14.250 1.0090 0.06175 0.05311 0.0241 0.0348 1.0000
14.500 1.0217 0.06377 0.05522 0.0242 0.0341 1.0000
14.750 1.0284 0.06638 0.05809 0.0243 0.0336 1.0000
15.000 1.0324 0.06927 0.06123 0.0243 0.0332 1.0000
15.250 1.0338 0.07242 0.06462 0.0241 0.0329 1.0000
15.500 1.0316 0.07596 0.06840 0.0237 0.0326 1.0000
15.750 1.0258 0.07993 0.07263 0.0231 0.0324 1.0000
16.000 1.0168 0.08437 0.07733 0.0221 0.0322 1.0000
16.250 1.0046 0.08933 0.08253 0.0207 0.0320 1.0000
16.500 0.9898 0.09482 0.08827 0.0187 0.0320 1.0000
16.750 0.9703 0.10128 0.09500 0.0160 0.0320 1.0000
17.000 0.9479 0.10861 0.10259 0.0124 0.0321 1.0000
17.250 0.9197 0.11757 0.11180 0.0074 0.0323 1.0000
17.500 0.8795 0.13005 0.12456 -0.0003 0.0326 1.0000
17.750 0.8170 0.15078 0.14552 -0.0132 0.0333 1.0000
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Polar data table (+)
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