NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 100,000 Max Cl/Cd: 43.03 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633218-il-100000.txt Download as CSV file: xf-naca633218-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7597 0.09137 0.08592 -0.0495 1.0000 0.0834
-14.500 -0.7926 0.08332 0.07773 -0.0536 1.0000 0.0827
-14.250 -0.8270 0.07619 0.07041 -0.0568 1.0000 0.0821
-14.000 -0.8568 0.07029 0.06432 -0.0590 1.0000 0.0816
-13.750 -0.8837 0.06522 0.05902 -0.0602 1.0000 0.0814
-13.500 -0.9063 0.06096 0.05453 -0.0605 1.0000 0.0814
-13.250 -0.9250 0.05727 0.05059 -0.0601 1.0000 0.0816
-13.000 -0.9408 0.05407 0.04713 -0.0592 1.0000 0.0821
-12.750 -0.9534 0.05134 0.04415 -0.0576 1.0000 0.0826
-12.500 -0.9658 0.04913 0.04165 -0.0554 1.0000 0.0834
-12.250 -0.9675 0.04658 0.03890 -0.0535 1.0000 0.0846
-12.000 -0.9427 0.04429 0.03670 -0.0541 1.0000 0.0876
-11.750 -0.9318 0.04257 0.03490 -0.0531 1.0000 0.0900
-11.500 -0.9248 0.04093 0.03310 -0.0515 1.0000 0.0925
-11.250 -0.9200 0.03943 0.03137 -0.0495 1.0000 0.0947
-11.000 -0.8999 0.03736 0.02923 -0.0491 1.0000 0.0977
-10.750 -0.8774 0.03595 0.02793 -0.0488 1.0000 0.1014
-10.500 -0.8722 0.03504 0.02699 -0.0462 1.0000 0.1045
-10.250 -0.8818 0.03459 0.02648 -0.0413 1.0000 0.1065
-10.000 -0.8916 0.03420 0.02598 -0.0364 0.9996 0.1082
-9.750 -0.8451 0.03235 0.02431 -0.0397 0.9951 0.1151
-9.500 -0.8055 0.03090 0.02274 -0.0428 0.9863 0.1239
-9.250 -0.7607 0.02930 0.02133 -0.0463 0.9807 0.1369
-9.000 -0.7234 0.02767 0.01989 -0.0490 0.9718 0.1550
-8.750 -0.6968 0.02582 0.01838 -0.0512 0.9610 0.1826
-8.500 -0.6813 0.02381 0.01679 -0.0520 0.9478 0.2252
-8.250 -0.6735 0.02207 0.01554 -0.0514 0.9341 0.2893
-8.000 -0.6619 0.02124 0.01515 -0.0500 0.9216 0.3598
-7.750 -0.6461 0.02125 0.01525 -0.0483 0.9092 0.4086
-7.500 -0.6227 0.02157 0.01553 -0.0472 0.8996 0.4438
-7.250 -0.5984 0.02211 0.01602 -0.0460 0.8896 0.4690
-7.000 -0.5709 0.02291 0.01679 -0.0447 0.8809 0.4901
-6.750 -0.5428 0.02384 0.01770 -0.0434 0.8723 0.5085
-6.500 -0.5123 0.02488 0.01868 -0.0421 0.8654 0.5250
-6.250 -0.4880 0.02560 0.01934 -0.0405 0.8560 0.5401
-6.000 -0.4528 0.02683 0.02053 -0.0392 0.8497 0.5513
-5.750 -0.4246 0.02763 0.02129 -0.0377 0.8403 0.5613
-5.500 -0.4061 0.02751 0.02101 -0.0362 0.8324 0.5752
-5.250 -0.3659 0.02898 0.02248 -0.0351 0.8259 0.5800
-5.000 -0.3525 0.02846 0.02183 -0.0336 0.8171 0.5939
-4.750 -0.3113 0.02977 0.02312 -0.0324 0.8119 0.5981
-4.500 -0.2932 0.02967 0.02293 -0.0311 0.8029 0.6098
-4.250 -0.2621 0.03013 0.02334 -0.0299 0.7964 0.6160
-4.000 -0.2316 0.03052 0.02367 -0.0288 0.7893 0.6222
-3.750 -0.2208 0.02958 0.02262 -0.0275 0.7795 0.6334
-3.500 -0.1882 0.02986 0.02281 -0.0264 0.7733 0.6378
-3.250 -0.1823 0.02862 0.02149 -0.0254 0.7625 0.6506
-3.000 -0.1500 0.02880 0.02159 -0.0242 0.7552 0.6539
-2.750 -0.1244 0.02880 0.02157 -0.0233 0.7461 0.6593
-2.500 -0.1123 0.02767 0.02032 -0.0227 0.7385 0.6703
-2.250 -0.0830 0.02774 0.02036 -0.0217 0.7311 0.6740
-2.000 -0.0591 0.02753 0.02012 -0.0208 0.7220 0.6800
-1.750 -0.0421 0.02651 0.01896 -0.0205 0.7153 0.6897
-1.500 -0.0162 0.02654 0.01902 -0.0193 0.7043 0.6936
-1.250 0.0097 0.02615 0.01852 -0.0186 0.6967 0.6996
-1.000 0.0259 0.02538 0.01771 -0.0182 0.6846 0.7089
-0.750 0.0532 0.02521 0.01749 -0.0172 0.6748 0.7128
-0.500 0.0771 0.02488 0.01712 -0.0164 0.6627 0.7186
-0.250 0.0965 0.02415 0.01631 -0.0163 0.6499 0.7277
0.000 0.1231 0.02395 0.01606 -0.0151 0.6383 0.7317
0.250 0.1472 0.02366 0.01572 -0.0143 0.6240 0.7372
0.500 0.1684 0.02307 0.01503 -0.0145 0.6086 0.7463
0.750 0.1928 0.02295 0.01488 -0.0132 0.5935 0.7505
1.000 0.2171 0.02277 0.01464 -0.0124 0.5793 0.7563
1.250 0.2414 0.02234 0.01404 -0.0129 0.5672 0.7650
1.500 0.2647 0.02232 0.01403 -0.0118 0.5538 0.7694
1.750 0.2893 0.02229 0.01394 -0.0111 0.5442 0.7757
2.000 0.3137 0.02211 0.01368 -0.0115 0.5352 0.7844
2.250 0.3385 0.02211 0.01364 -0.0106 0.5288 0.7893
2.500 0.3624 0.02213 0.01368 -0.0102 0.5216 0.7960
2.750 0.3877 0.02204 0.01354 -0.0103 0.5164 0.8042
3.250 0.4365 0.02215 0.01367 -0.0095 0.5080 0.8188
3.500 0.4601 0.02221 0.01379 -0.0090 0.5043 0.8254
3.750 0.4842 0.02230 0.01393 -0.0085 0.5014 0.8330
4.000 0.5089 0.02237 0.01401 -0.0084 0.4991 0.8416
4.250 0.5334 0.02246 0.01414 -0.0078 0.4970 0.8491
4.500 0.5591 0.02254 0.01422 -0.0078 0.4951 0.8582
4.750 0.5808 0.02271 0.01451 -0.0069 0.4928 0.8660
5.000 0.6018 0.02293 0.01485 -0.0063 0.4906 0.8761
5.250 0.6231 0.02313 0.01519 -0.0054 0.4883 0.8851
5.500 0.6446 0.02331 0.01547 -0.0048 0.4859 0.8952
5.750 0.6676 0.02349 0.01575 -0.0042 0.4837 0.9056
6.000 0.6932 0.02368 0.01604 -0.0042 0.4818 0.9157
6.250 0.7191 0.02385 0.01631 -0.0043 0.4801 0.9272
6.500 0.7549 0.02384 0.01630 -0.0057 0.4767 0.9371
6.750 0.7801 0.02418 0.01690 -0.0064 0.4704 0.9489
7.000 0.8209 0.02403 0.01680 -0.0090 0.4632 0.9588
7.250 0.8636 0.02407 0.01691 -0.0121 0.4569 0.9686
7.500 0.9114 0.02402 0.01701 -0.0164 0.4463 0.9764
7.750 0.9569 0.02387 0.01694 -0.0203 0.4326 0.9856
8.000 1.0006 0.02362 0.01674 -0.0239 0.4157 0.9970
8.250 1.0113 0.02350 0.01658 -0.0218 0.4051 1.0000
8.500 0.9991 0.02362 0.01680 -0.0163 0.3980 1.0000
8.750 1.0080 0.02365 0.01683 -0.0140 0.3860 1.0000
9.000 1.0216 0.02382 0.01701 -0.0127 0.3706 1.0000
9.250 1.0346 0.02415 0.01733 -0.0114 0.3525 1.0000
9.500 1.0502 0.02470 0.01759 -0.0102 0.3298 1.0000
9.750 1.0568 0.02570 0.01845 -0.0081 0.3051 1.0000
10.000 1.0426 0.02692 0.02007 -0.0043 0.2800 1.0000
10.250 1.0243 0.02872 0.02168 -0.0015 0.2243 1.0000
10.500 1.0050 0.03168 0.02413 0.0009 0.2095 1.0000
10.750 0.9997 0.03440 0.02653 0.0030 0.1895 1.0000
11.000 1.0041 0.03664 0.02864 0.0043 0.1701 1.0000
11.250 1.0043 0.03885 0.03093 0.0052 0.1557 1.0000
11.500 1.0056 0.04098 0.03306 0.0058 0.1444 1.0000
11.750 1.0086 0.04305 0.03513 0.0063 0.1347 1.0000
12.000 1.0188 0.04475 0.03681 0.0069 0.1257 1.0000
12.250 1.0349 0.04606 0.03797 0.0075 0.1177 1.0000
12.500 1.0516 0.04740 0.03931 0.0080 0.1106 1.0000
12.750 1.0778 0.04849 0.04029 0.0085 0.1043 1.0000
13.000 1.0937 0.05015 0.04206 0.0089 0.0995 1.0000
13.250 1.1290 0.05125 0.04292 0.0090 0.0938 1.0000
13.500 1.1356 0.05346 0.04540 0.0095 0.0909 1.0000
13.750 1.1467 0.05558 0.04767 0.0098 0.0875 1.0000
14.000 1.1651 0.05727 0.04931 0.0099 0.0841 1.0000
14.250 1.1819 0.05979 0.05191 0.0101 0.0812 1.0000
14.500 1.1779 0.06288 0.05531 0.0104 0.0794 1.0000
14.750 1.1764 0.06600 0.05867 0.0104 0.0776 1.0000
15.000 1.1799 0.06882 0.06162 0.0104 0.0756 1.0000
15.250 1.1858 0.07158 0.06445 0.0102 0.0738 1.0000
15.500 1.2051 0.07481 0.06765 0.0101 0.0718 1.0000
15.750 1.1839 0.07953 0.07269 0.0094 0.0715 1.0000
16.000 1.1610 0.08482 0.07829 0.0081 0.0713 1.0000
16.250 1.1362 0.09074 0.08450 0.0062 0.0712 1.0000
16.500 1.1089 0.09747 0.09149 0.0035 0.0712 1.0000
16.750 1.0787 0.10515 0.09942 -0.0001 0.0714 1.0000
17.000 1.0475 0.11374 0.10822 -0.0046 0.0717 1.0000
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