UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Reynolds number: 200,000 Max Cl/Cd: 37.17 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua79sf18-il-200000.txt Download as CSV file: xf-ua79sf18-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.0176 0.11260 0.10847 -0.1533 0.8705 0.0415
-12.750 -0.0235 0.10876 0.10468 -0.1565 0.8702 0.0421
-12.500 -0.0261 0.10478 0.10073 -0.1590 0.8700 0.0422
-12.250 -0.0304 0.10029 0.09628 -0.1619 0.8698 0.0423
-12.000 -0.0204 0.09702 0.09304 -0.1596 0.8697 0.0442
-11.750 -0.0139 0.09476 0.09079 -0.1598 0.8692 0.0454
-11.500 -0.0113 0.09209 0.08814 -0.1605 0.8686 0.0467
-11.250 -0.0132 0.08881 0.08490 -0.1619 0.8682 0.0481
-11.000 -0.0196 0.08489 0.08101 -0.1637 0.8671 0.0495
-10.750 -0.0336 0.07952 0.07569 -0.1669 0.8659 0.0500
-10.500 -0.0570 0.07438 0.07054 -0.1699 0.8652 0.0506
-10.250 -0.0798 0.07101 0.06716 -0.1707 0.8648 0.0503
-10.000 -0.1054 0.06861 0.06473 -0.1698 0.8643 0.0500
-9.750 -0.1336 0.06697 0.06305 -0.1672 0.8633 0.0501
-9.500 -0.1632 0.06618 0.06223 -0.1630 0.8623 0.0502
-9.250 -0.2009 0.06739 0.06348 -0.1553 0.8620 0.0493
-8.500 -0.4857 0.09397 0.09091 -0.0834 0.9087 0.0411
-8.250 -0.5104 0.09134 0.08816 -0.0814 0.9041 0.0410
-8.000 -0.5376 0.08918 0.08591 -0.0765 0.8947 0.0411
-7.750 -0.5538 0.08771 0.08403 -0.0746 0.8898 0.0420
-7.500 -0.5748 0.08597 0.08211 -0.0690 0.8809 0.0421
-7.250 -0.5833 0.08100 0.07681 -0.0677 0.8770 0.0426
-7.000 -0.5765 0.07403 0.06990 -0.0688 0.8759 0.0442
-6.750 -0.5584 0.07146 0.06730 -0.0699 0.8748 0.0458
-6.500 -0.5769 0.06926 0.06503 -0.0634 0.8651 0.0463
-6.250 -0.5619 0.06674 0.06231 -0.0634 0.8630 0.0495
-4.750 -0.4783 0.05023 0.04347 -0.0506 0.8402 0.0290
-4.500 -0.4518 0.04675 0.03961 -0.0501 0.8383 0.0245
-4.250 -0.4191 0.04500 0.03735 -0.0496 0.8369 0.0212
-4.000 -0.3862 0.04453 0.03666 -0.0503 0.8358 0.0208
-3.750 -0.3886 0.04308 0.03515 -0.0456 0.8286 0.0212
-3.500 -0.3626 0.04217 0.03422 -0.0455 0.8255 0.0223
-3.250 -0.3319 0.04204 0.03408 -0.0465 0.8236 0.0254
-3.000 -0.2994 0.04189 0.03388 -0.0475 0.8224 0.0270
-2.750 -0.3033 0.04105 0.03302 -0.0429 0.8137 0.0274
-2.500 -0.2732 0.04071 0.03259 -0.0435 0.8110 0.0294
-2.250 -0.2395 0.04053 0.03230 -0.0449 0.8095 0.0342
-2.000 -0.2383 0.04009 0.03181 -0.0413 0.8014 0.0396
-1.750 -0.2260 0.03791 0.03230 -0.0391 0.7982 0.6744
-1.500 -0.2007 0.03956 0.03423 -0.0359 0.7960 0.7339
-1.250 -0.2075 0.03984 0.03465 -0.0287 0.7861 0.7614
-1.000 -0.1875 0.04114 0.03602 -0.0241 0.7831 0.7915
-0.750 -0.1802 0.04112 0.03596 -0.0199 0.7722 0.8048
-0.500 -0.1387 0.04058 0.03525 -0.0209 0.7585 0.8103
-0.250 -0.1068 0.04043 0.03491 -0.0220 0.7500 0.8139
0.000 -0.0749 0.04043 0.03477 -0.0234 0.7452 0.8161
0.250 -0.0357 0.04049 0.03470 -0.0255 0.7430 0.8175
0.500 0.0065 0.04070 0.03478 -0.0281 0.7418 0.8185
0.750 0.0083 0.04062 0.03467 -0.0252 0.7315 0.8202
1.000 0.0481 0.04068 0.03461 -0.0275 0.7297 0.8211
1.250 0.0567 0.04088 0.03478 -0.0258 0.7208 0.8221
1.500 0.0911 0.04095 0.03476 -0.0275 0.7184 0.8230
1.750 0.1295 0.04098 0.03471 -0.0297 0.7169 0.8239
2.000 0.1381 0.04129 0.03499 -0.0280 0.7076 0.8250
2.250 0.1729 0.04131 0.03494 -0.0298 0.7053 0.8256
2.500 0.2106 0.04130 0.03487 -0.0319 0.7038 0.8265
2.750 0.2506 0.04122 0.03474 -0.0342 0.7028 0.8274
3.000 0.2563 0.04154 0.03505 -0.0322 0.6921 0.8288
3.250 0.2952 0.04130 0.03478 -0.0342 0.6905 0.8298
3.500 0.3351 0.04097 0.03443 -0.0363 0.6895 0.8305
3.750 0.3406 0.04142 0.03489 -0.0342 0.6790 0.8313
4.000 0.3775 0.04116 0.03462 -0.0359 0.6775 0.8318
4.250 0.4156 0.04081 0.03428 -0.0377 0.6765 0.8326
4.500 0.4225 0.04133 0.03483 -0.0358 0.6662 0.8338
4.750 0.4605 0.04086 0.03437 -0.0375 0.6647 0.8344
5.000 0.5003 0.04025 0.03379 -0.0395 0.6636 0.8351
5.250 0.5099 0.04071 0.03428 -0.0379 0.6532 0.8361
5.500 0.5478 0.04009 0.03370 -0.0395 0.6516 0.8369
5.750 0.5863 0.03947 0.03313 -0.0413 0.6506 0.8379
6.000 0.5949 0.04011 0.03382 -0.0396 0.6399 0.8392
6.250 0.6321 0.03948 0.03325 -0.0412 0.6384 0.8403
6.500 0.6702 0.03876 0.03258 -0.0428 0.6372 0.8416
6.750 0.6809 0.03937 0.03327 -0.0414 0.6266 0.8432
7.000 0.7171 0.03858 0.03258 -0.0426 0.6249 0.8447
7.250 0.7544 0.03769 0.03180 -0.0439 0.6236 0.8465
7.500 0.7988 0.03573 0.02995 -0.0454 0.6215 0.8484
8.250 0.9254 0.02743 0.02158 -0.0469 0.5503 0.8557
8.500 0.9644 0.02614 0.02004 -0.0478 0.5030 0.8582
8.750 0.9797 0.02636 0.01998 -0.0461 0.4527 0.8612
9.000 0.9829 0.02748 0.02089 -0.0433 0.4102 0.8653
9.250 0.9646 0.02994 0.02281 -0.0384 0.3338 0.8705
9.500 0.9566 0.03205 0.02459 -0.0349 0.2771 0.8758
9.750 0.9499 0.03427 0.02645 -0.0319 0.2160 0.8826
10.000 0.9372 0.03702 0.02865 -0.0286 0.1316 0.8906
10.250 0.9263 0.03985 0.03096 -0.0257 0.0503 0.9016
10.500 0.9282 0.04199 0.03293 -0.0241 0.0163 0.9179
10.750 0.9489 0.04326 0.03439 -0.0253 0.0143 0.9502
11.000 0.9610 0.04447 0.03573 -0.0247 0.0134 1.0000
11.250 0.9755 0.04588 0.03724 -0.0246 0.0133 1.0000
11.500 0.9876 0.04744 0.03894 -0.0242 0.0132 1.0000
11.750 0.9978 0.04915 0.04079 -0.0236 0.0129 1.0000
12.000 1.0068 0.05097 0.04277 -0.0229 0.0129 1.0000
12.250 1.0138 0.05300 0.04494 -0.0221 0.0129 1.0000
12.500 1.0183 0.05529 0.04737 -0.0213 0.0130 1.0000
12.750 1.0219 0.05770 0.04990 -0.0204 0.0130 1.0000
13.000 1.0235 0.06035 0.05266 -0.0196 0.0131 1.0000
13.250 1.0249 0.06306 0.05547 -0.0187 0.0132 1.0000
13.500 1.0274 0.06566 0.05814 -0.0179 0.0132 1.0000
13.750 1.0320 0.06802 0.06057 -0.0172 0.0134 1.0000
14.000 1.0410 0.06994 0.06255 -0.0166 0.0136 1.0000
14.250 1.0529 0.07158 0.06424 -0.0161 0.0138 1.0000
14.500 1.0664 0.07308 0.06581 -0.0157 0.0141 1.0000
14.750 1.0808 0.07450 0.06732 -0.0153 0.0146 1.0000
15.000 1.1024 0.07524 0.06821 -0.0145 0.0155 1.0000
15.250 1.1343 0.07539 0.06861 -0.0135 0.0171 1.0000
15.500 1.2126 0.07512 0.06852 -0.0136 0.0207 1.0000
15.750 1.2097 0.07718 0.07078 -0.0126 0.0216 1.0000
16.000 0.9946 0.08349 0.07829 -0.0073 0.0185 1.0000
16.250 1.0314 0.08330 0.07826 -0.0062 0.0207 1.0000
16.500 1.0227 0.08615 0.08132 -0.0066 0.0214 1.0000
16.750 1.0030 0.09093 0.08658 -0.0070 0.0234 1.0000
17.000 0.9797 0.09630 0.09233 -0.0083 0.0247 1.0000
17.250 0.9583 0.10158 0.09790 -0.0100 0.0257 1.0000
17.500 0.9367 0.10703 0.10358 -0.0123 0.0263 1.0000
17.750 0.9134 0.11291 0.10969 -0.0152 0.0268 1.0000
18.000 0.8895 0.11919 0.11616 -0.0187 0.0269 1.0000
18.250 0.8638 0.12609 0.12326 -0.0229 0.0270 1.0000
18.500 0.8385 0.13339 0.13075 -0.0278 0.0266 1.0000
18.750 0.8093 0.14205 0.13958 -0.0336 0.0262 1.0000
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Polar data table (+)
Polar graphs
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